Cycle Dump
Uploaded by
trainingcenter142Cycle Dump
Uploaded by
trainingcenter142•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
X-Plane, by Austin Meyer
122103
Simulating Aircraft/Laminar Research/BELL 412 EPI/Bell412.acf
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
x location positive aft x force positive right pitch/alpha pos nose up
y location positive right y force positive up roll pos right
z location positive up z force positive aft yaw/beta pos nose right
elevator, aileron, spoiler positive control surface up
rudder positive control surface right
drag-yaw positive control surface deployed
pitch cyclic prop pitch positive request nose up
roll cyclic prop pitch positive request nose right
Finite-wing and build-up for prop 1: Wing area for this wing is 2.5043 m*m.
After any wing-joining, our area is 2.50 m*m.
After any wing-joining, our semi-length is 7.01 m.
After any wing-joining, our root chord is 0.41 m.
After any wing-joining, our tip chord is 0.41 m.
After any wing-joining, our mean aero sweep is 0.1 deg.
After any wing-joining, our aspect ratio is 39.2491.
After any wing-joining, spanwise centroid is 0.5180 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.7407.
Finite-wing and build-up for prop 2: Wing area for this wing is 0.3368 m*m.
After any wing-joining, our area is 0.34 m*m.
After any wing-joining, our semi-length is 1.30 m.
After any wing-joining, our root chord is 0.29 m.
After any wing-joining, our tip chord is 0.29 m.
After any wing-joining, our mean aero sweep is 1.9 deg.
After any wing-joining, our aspect ratio is 9.9658.
After any wing-joining, spanwise centroid is 0.5511 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9245.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Vert Stab 2: Wing area for this wing is 1.1343 m*m.
After any wing-joining, our area is 1.13 m*m.
After any wing-joining, our semi-length is 1.89 m.
After any wing-joining, our root chord is 1.07 m.
After any wing-joining, our tip chord is 0.55 m.
After any wing-joining, our mean aero sweep is 42.0 deg.
After any wing-joining, our aspect ratio is 3.4774.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9783.
The prop 1 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.06, rad2= 0.70, ring area is 1.5404 m*m.
element number 1, rad1= 0.70, rad2= 1.40, ring area is 4.6238 m*m.
element number 2, rad1= 1.40, rad2= 2.10, ring area is 7.7198 m*m.
element number 3, rad1= 2.10, rad2= 2.80, ring area is 10.8077 m*m.
element number 4, rad1= 2.80, rad2= 3.51, ring area is 13.8956 m*m.
element number 5, rad1= 3.51, rad2= 4.21, ring area is 16.9835 m*m.
element number 6, rad1= 4.21, rad2= 4.91, ring area is 20.0714 m*m.
element number 7, rad1= 4.91, rad2= 5.61, ring area is 23.1594 m*m.
element number 8, rad1= 5.61, rad2= 6.31, ring area is 26.2481 m*m.
element number 9, rad1= 6.31, rad2= 7.01, ring area is 29.3425 m*m.
TOTAL DISC AREA=154.4039 m*m
en=0, el=0, element_mass= 6.774 veh_prop_ptr(en)->prop_mass=6.774,
rad_arm_mtr= 0.50, veh_prop_ptr(en)->prop_mi_rpm= 1.664 kg*m*m
en=0, el=1, element_mass= 19.432 veh_prop_ptr(en)->prop_mass=26.206,
rad_arm_mtr= 1.20, veh_prop_ptr(en)->prop_mi_rpm= 29.492 kg*m*m
en=0, el=2, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=59.518,
rad_arm_mtr= 1.90, veh_prop_ptr(en)->prop_mi_rpm=149.461 kg*m*m
en=0, el=3, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=92.831,
rad_arm_mtr= 2.60, veh_prop_ptr(en)->prop_mi_rpm=374.439 kg*m*m
en=0, el=4, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=126.144,
rad_arm_mtr= 3.30, veh_prop_ptr(en)->prop_mi_rpm=737.168 kg*m*m
en=0, el=5, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=159.456,
rad_arm_mtr= 4.00, veh_prop_ptr(en)->prop_mi_rpm=1270.392 kg*m*m
en=0, el=6, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=192.769,
rad_arm_mtr= 4.70, veh_prop_ptr(en)->prop_mi_rpm=2006.854 kg*m*m
en=0, el=7, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=226.081,
rad_arm_mtr= 5.40, veh_prop_ptr(en)->prop_mi_rpm=2979.298 kg*m*m
en=0, el=8, element_mass= 23.791 veh_prop_ptr(en)->prop_mass=249.873,
rad_arm_mtr= 6.10, veh_prop_ptr(en)->prop_mi_rpm=3865.719 kg*m*m
en=0, el=9, element_mass= 10.438 veh_prop_ptr(en)->prop_mass=260.310,
rad_arm_mtr= 6.80, veh_prop_ptr(en)->prop_mi_rpm=4349.075 kg*m*m
BEFORE any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The mass of prop 1 tip weights is 0.0 kg total (all blades) centered at
location 6.3 m
AFTER any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The prop 2 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.04, rad2= 0.14, ring area is 0.0574 m*m.
element number 1, rad1= 0.14, rad2= 0.26, ring area is 0.1474 m*m.
element number 2, rad1= 0.26, rad2= 0.39, ring area is 0.2636 m*m.
element number 3, rad1= 0.39, rad2= 0.52, ring area is 0.3690 m*m.
element number 4, rad1= 0.52, rad2= 0.65, ring area is 0.4745 m*m.
element number 5, rad1= 0.65, rad2= 0.78, ring area is 0.5799 m*m.
element number 6, rad1= 0.78, rad2= 0.91, ring area is 0.6853 m*m.
element number 7, rad1= 0.91, rad2= 1.04, ring area is 0.7908 m*m.
element number 8, rad1= 1.04, rad2= 1.17, ring area is 0.8962 m*m.
element number 9, rad1= 1.17, rad2= 1.30, ring area is 1.0016 m*m.
TOTAL DISC AREA= 5.2718 m*m
en=1, el=0, element_mass= 0.148 veh_prop_ptr(en)->prop_mass=0.148,
rad_arm_mtr= 0.09, veh_prop_ptr(en)->prop_mi_rpm= 0.001 kg*m*m
en=1, el=1, element_mass= 0.657 veh_prop_ptr(en)->prop_mass=0.806,
rad_arm_mtr= 0.22, veh_prop_ptr(en)->prop_mi_rpm= 0.033 kg*m*m
en=1, el=2, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=2.396,
rad_arm_mtr= 0.35, veh_prop_ptr(en)->prop_mi_rpm= 0.229 kg*m*m
en=1, el=3, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=3.986,
rad_arm_mtr= 0.48, veh_prop_ptr(en)->prop_mi_rpm= 0.596 kg*m*m
en=1, el=4, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=5.576,
rad_arm_mtr= 0.61, veh_prop_ptr(en)->prop_mi_rpm= 1.187 kg*m*m
en=1, el=5, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=7.166,
rad_arm_mtr= 0.74, veh_prop_ptr(en)->prop_mi_rpm= 2.056 kg*m*m
en=1, el=6, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=8.756,
rad_arm_mtr= 0.87, veh_prop_ptr(en)->prop_mi_rpm= 3.256 kg*m*m
en=1, el=7, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=10.346,
rad_arm_mtr= 1.00, veh_prop_ptr(en)->prop_mi_rpm= 4.841 kg*m*m
en=1, el=8, element_mass= 1.391 veh_prop_ptr(en)->prop_mass=11.737,
rad_arm_mtr= 1.13, veh_prop_ptr(en)->prop_mi_rpm= 6.611 kg*m*m
en=1, el=9, element_mass= 1.192 veh_prop_ptr(en)->prop_mass=12.929,
rad_arm_mtr= 1.26, veh_prop_ptr(en)->prop_mi_rpm= 8.496 kg*m*m
BEFORE any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
AFTER any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Engine # 0 is mass 248.206 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Engine # 1 is mass 248.206 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Prop # 0 is mass 260.310 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Prop # 1 is mass 12.929 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Fuel tank # 0 is mass 6.026 kg at x= 0.00, y= -0.06, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 1 is mass 3.515 kg at x= 0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 2 is mass 3.515 kg at x= -0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 3 is mass 10.545 kg at x= 0.00, y= -0.52, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 4 is mass 2.511 kg at x= 0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 5 is mass 2.511 kg at x= -0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 6 is mass 12.553 kg at x= 0.00, y= -0.98, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 7 is mass 4.519 kg at x= 0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Fuel tank # 8 is mass 4.519 kg at x= -0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Right Stab Running wetted area 0.3019 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Right Stab Running wetted area 0.6037 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Vert Stab 2 Running wetted area 0.9667 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.15 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 7.07 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 7.02 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Body 1 (fuselage):
The frontal area is 4.0966 m*m.
The side area is 14.3132 m*m.
The top area is 16.3570 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is 0.02 m.
The longitudinal centroid for lift at 0 slip is -3.85 m.
The longitudinal centroid for lift at 180 slip is 2.18 meters
Running wetted area 53.9898 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.98 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.11 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.09 m, based on mass-
distribution across the shell of the craft.
Body 22 (nacele):
The frontal area is 0.0188 m*m.
The side area is 0.1896 m*m.
The top area is 0.1911 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is 0.00 m.
The longitudinal centroid for lift at 180 slip is 0.61 meters
Running wetted area 54.6234 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.99 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.10 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.07 m, based on mass-
distribution across the shell of the craft.
Body 23 (hgiRaN tllec):
The frontal area is 0.0167 m*m.
The side area is 0.0849 m*m.
The top area is 0.0956 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is -0.46 m.
The longitudinal centroid for lift at 180 slip is -0.15 meters
Running wetted area 54.9388 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
Sum of all engines have mass of 496.41 kg ( 16% of total):
The radius of gyration of the engines in roll is 1.91 m, based on all
engine masses and locations.
The radius of gyration of the engines in pitch is 6.57 m, based on all
engine masses and locations.
The radius of gyration of the engines in yaw is 6.30 m, based on all
engine masses and locations.
Sum of all props have mass of 273.24 kg ( 9% of total):
The radius of gyration of the props in roll is 1.81 m, based on all prop
masses and locations.
The radius of gyration of the props in pitch is 2.65 m, based on all prop
masses and locations.
The radius of gyration of the props in yaw is 1.94 m, based on all prop
masses and locations.
Sum of all tanks have mass of 50.21 kg ( 2% of total):
The radius of gyration of the tanks in roll is 1.04 m, based on all tank
masses and locations.
The radius of gyration of the tanks in pitch is 1.08 m, based on all tank
masses and locations.
The radius of gyration of the tanks in yaw is 0.76 m, based on all tank
masses and locations.
Remainder of the craft has mass 2258.21 ( 73% of total):
The radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
As specified in the manual radius of gyration in the Weight and Balance screen in
Plane Maker:
The radius of gyration in roll is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
The radius of gyration in pitch is 4.07 m. (that's moment of inertia
50965.027 kg*m*m).
The radius of gyration in yaw is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
Wing area : 10.6907 m*m. (For wings 1 through 4 only, each times the
cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC : 0.26 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
Long-arm of 25% MAC : 0.00 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
X-Plane, by Austin Meyer
122103
Simulating Aircraft/Laminar Research/BELL 412 EPI/Bell412.acf
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
x location positive aft x force positive right pitch/alpha pos nose up
y location positive right y force positive up roll pos right
z location positive up z force positive aft yaw/beta pos nose right
elevator, aileron, spoiler positive control surface up
rudder positive control surface right
drag-yaw positive control surface deployed
pitch cyclic prop pitch positive request nose up
roll cyclic prop pitch positive request nose right
Finite-wing and build-up for prop 1: Wing area for this wing is 2.5043 m*m.
After any wing-joining, our area is 2.50 m*m.
After any wing-joining, our semi-length is 7.01 m.
After any wing-joining, our root chord is 0.41 m.
After any wing-joining, our tip chord is 0.41 m.
After any wing-joining, our mean aero sweep is 0.1 deg.
After any wing-joining, our aspect ratio is 39.2491.
After any wing-joining, spanwise centroid is 0.5180 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.7407.
Finite-wing and build-up for prop 2: Wing area for this wing is 0.3368 m*m.
After any wing-joining, our area is 0.34 m*m.
After any wing-joining, our semi-length is 1.30 m.
After any wing-joining, our root chord is 0.29 m.
After any wing-joining, our tip chord is 0.29 m.
After any wing-joining, our mean aero sweep is 1.9 deg.
After any wing-joining, our aspect ratio is 9.9658.
After any wing-joining, spanwise centroid is 0.5511 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9245.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Vert Stab 2: Wing area for this wing is 1.1343 m*m.
After any wing-joining, our area is 1.13 m*m.
After any wing-joining, our semi-length is 1.89 m.
After any wing-joining, our root chord is 1.07 m.
After any wing-joining, our tip chord is 0.55 m.
After any wing-joining, our mean aero sweep is 42.0 deg.
After any wing-joining, our aspect ratio is 3.4774.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9783.
The prop 1 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.06, rad2= 0.70, ring area is 1.5404 m*m.
element number 1, rad1= 0.70, rad2= 1.40, ring area is 4.6238 m*m.
element number 2, rad1= 1.40, rad2= 2.10, ring area is 7.7198 m*m.
element number 3, rad1= 2.10, rad2= 2.80, ring area is 10.8077 m*m.
element number 4, rad1= 2.80, rad2= 3.51, ring area is 13.8956 m*m.
element number 5, rad1= 3.51, rad2= 4.21, ring area is 16.9835 m*m.
element number 6, rad1= 4.21, rad2= 4.91, ring area is 20.0714 m*m.
element number 7, rad1= 4.91, rad2= 5.61, ring area is 23.1594 m*m.
element number 8, rad1= 5.61, rad2= 6.31, ring area is 26.2481 m*m.
element number 9, rad1= 6.31, rad2= 7.01, ring area is 29.3425 m*m.
TOTAL DISC AREA=154.4039 m*m
en=0, el=0, element_mass= 6.774 veh_prop_ptr(en)->prop_mass=6.774,
rad_arm_mtr= 0.50, veh_prop_ptr(en)->prop_mi_rpm= 1.664 kg*m*m
en=0, el=1, element_mass= 19.432 veh_prop_ptr(en)->prop_mass=26.206,
rad_arm_mtr= 1.20, veh_prop_ptr(en)->prop_mi_rpm= 29.492 kg*m*m
en=0, el=2, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=59.518,
rad_arm_mtr= 1.90, veh_prop_ptr(en)->prop_mi_rpm=149.461 kg*m*m
en=0, el=3, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=92.831,
rad_arm_mtr= 2.60, veh_prop_ptr(en)->prop_mi_rpm=374.439 kg*m*m
en=0, el=4, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=126.144,
rad_arm_mtr= 3.30, veh_prop_ptr(en)->prop_mi_rpm=737.168 kg*m*m
en=0, el=5, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=159.456,
rad_arm_mtr= 4.00, veh_prop_ptr(en)->prop_mi_rpm=1270.392 kg*m*m
en=0, el=6, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=192.769,
rad_arm_mtr= 4.70, veh_prop_ptr(en)->prop_mi_rpm=2006.854 kg*m*m
en=0, el=7, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=226.081,
rad_arm_mtr= 5.40, veh_prop_ptr(en)->prop_mi_rpm=2979.298 kg*m*m
en=0, el=8, element_mass= 23.791 veh_prop_ptr(en)->prop_mass=249.873,
rad_arm_mtr= 6.10, veh_prop_ptr(en)->prop_mi_rpm=3865.719 kg*m*m
en=0, el=9, element_mass= 10.438 veh_prop_ptr(en)->prop_mass=260.310,
rad_arm_mtr= 6.80, veh_prop_ptr(en)->prop_mi_rpm=4349.075 kg*m*m
BEFORE any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The mass of prop 1 tip weights is 0.0 kg total (all blades) centered at
location 6.3 m
AFTER any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The prop 2 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.04, rad2= 0.14, ring area is 0.0574 m*m.
element number 1, rad1= 0.14, rad2= 0.26, ring area is 0.1474 m*m.
element number 2, rad1= 0.26, rad2= 0.39, ring area is 0.2636 m*m.
element number 3, rad1= 0.39, rad2= 0.52, ring area is 0.3690 m*m.
element number 4, rad1= 0.52, rad2= 0.65, ring area is 0.4745 m*m.
element number 5, rad1= 0.65, rad2= 0.78, ring area is 0.5799 m*m.
element number 6, rad1= 0.78, rad2= 0.91, ring area is 0.6853 m*m.
element number 7, rad1= 0.91, rad2= 1.04, ring area is 0.7908 m*m.
element number 8, rad1= 1.04, rad2= 1.17, ring area is 0.8962 m*m.
element number 9, rad1= 1.17, rad2= 1.30, ring area is 1.0016 m*m.
TOTAL DISC AREA= 5.2718 m*m
en=1, el=0, element_mass= 0.148 veh_prop_ptr(en)->prop_mass=0.148,
rad_arm_mtr= 0.09, veh_prop_ptr(en)->prop_mi_rpm= 0.001 kg*m*m
en=1, el=1, element_mass= 0.657 veh_prop_ptr(en)->prop_mass=0.806,
rad_arm_mtr= 0.22, veh_prop_ptr(en)->prop_mi_rpm= 0.033 kg*m*m
en=1, el=2, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=2.396,
rad_arm_mtr= 0.35, veh_prop_ptr(en)->prop_mi_rpm= 0.229 kg*m*m
en=1, el=3, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=3.986,
rad_arm_mtr= 0.48, veh_prop_ptr(en)->prop_mi_rpm= 0.596 kg*m*m
en=1, el=4, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=5.576,
rad_arm_mtr= 0.61, veh_prop_ptr(en)->prop_mi_rpm= 1.187 kg*m*m
en=1, el=5, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=7.166,
rad_arm_mtr= 0.74, veh_prop_ptr(en)->prop_mi_rpm= 2.056 kg*m*m
en=1, el=6, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=8.756,
rad_arm_mtr= 0.87, veh_prop_ptr(en)->prop_mi_rpm= 3.256 kg*m*m
en=1, el=7, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=10.346,
rad_arm_mtr= 1.00, veh_prop_ptr(en)->prop_mi_rpm= 4.841 kg*m*m
en=1, el=8, element_mass= 1.391 veh_prop_ptr(en)->prop_mass=11.737,
rad_arm_mtr= 1.13, veh_prop_ptr(en)->prop_mi_rpm= 6.611 kg*m*m
en=1, el=9, element_mass= 1.192 veh_prop_ptr(en)->prop_mass=12.929,
rad_arm_mtr= 1.26, veh_prop_ptr(en)->prop_mi_rpm= 8.496 kg*m*m
BEFORE any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
AFTER any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Engine # 0 is mass 248.206 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Engine # 1 is mass 248.206 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Prop # 0 is mass 260.310 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Prop # 1 is mass 12.929 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Fuel tank # 0 is mass 6.026 kg at x= 0.00, y= -0.06, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 1 is mass 3.515 kg at x= 0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 2 is mass 3.515 kg at x= -0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 3 is mass 10.545 kg at x= 0.00, y= -0.52, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 4 is mass 2.511 kg at x= 0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 5 is mass 2.511 kg at x= -0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 6 is mass 12.553 kg at x= 0.00, y= -0.98, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 7 is mass 4.519 kg at x= 0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Fuel tank # 8 is mass 4.519 kg at x= -0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Right Stab Running wetted area 0.3019 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Right Stab Running wetted area 0.6037 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Vert Stab 2 Running wetted area 0.9667 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.15 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 7.07 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 7.02 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Body 1 (fuselage):
The frontal area is 4.0966 m*m.
The side area is 14.3132 m*m.
The top area is 16.3570 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is 0.02 m.
The longitudinal centroid for lift at 0 slip is -3.85 m.
The longitudinal centroid for lift at 180 slip is 2.18 meters
Running wetted area 53.9898 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.98 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.11 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.09 m, based on mass-
distribution across the shell of the craft.
Body 22 (nacele):
The frontal area is 0.0188 m*m.
The side area is 0.1896 m*m.
The top area is 0.1911 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is 0.00 m.
The longitudinal centroid for lift at 180 slip is 0.61 meters
Running wetted area 54.6234 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.99 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.10 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.07 m, based on mass-
distribution across the shell of the craft.
Body 23 (hgiRaN tllec):
The frontal area is 0.0167 m*m.
The side area is 0.0849 m*m.
The top area is 0.0956 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is -0.46 m.
The longitudinal centroid for lift at 180 slip is -0.15 meters
Running wetted area 54.9388 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
Sum of all engines have mass of 496.41 kg ( 16% of total):
The radius of gyration of the engines in roll is 1.91 m, based on all
engine masses and locations.
The radius of gyration of the engines in pitch is 6.57 m, based on all
engine masses and locations.
The radius of gyration of the engines in yaw is 6.30 m, based on all
engine masses and locations.
Sum of all props have mass of 273.24 kg ( 9% of total):
The radius of gyration of the props in roll is 1.81 m, based on all prop
masses and locations.
The radius of gyration of the props in pitch is 2.65 m, based on all prop
masses and locations.
The radius of gyration of the props in yaw is 1.94 m, based on all prop
masses and locations.
Sum of all tanks have mass of 50.21 kg ( 2% of total):
The radius of gyration of the tanks in roll is 1.04 m, based on all tank
masses and locations.
The radius of gyration of the tanks in pitch is 1.08 m, based on all tank
masses and locations.
The radius of gyration of the tanks in yaw is 0.76 m, based on all tank
masses and locations.
Remainder of the craft has mass 2258.21 ( 73% of total):
The radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
As specified in the manual radius of gyration in the Weight and Balance screen in
Plane Maker:
The radius of gyration in roll is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
The radius of gyration in pitch is 4.07 m. (that's moment of inertia
50965.027 kg*m*m).
The radius of gyration in yaw is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
Wing area : 10.6907 m*m. (For wings 1 through 4 only, each times the
cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC : 0.26 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
Long-arm of 25% MAC : 0.00 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
X-Plane, by Austin Meyer
122103
Simulating Aircraft/Laminar Research/BELL 412 EPI/Bell412.acf
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
x location positive aft x force positive right pitch/alpha pos nose up
y location positive right y force positive up roll pos right
z location positive up z force positive aft yaw/beta pos nose right
elevator, aileron, spoiler positive control surface up
rudder positive control surface right
drag-yaw positive control surface deployed
pitch cyclic prop pitch positive request nose up
roll cyclic prop pitch positive request nose right
Finite-wing and build-up for prop 1: Wing area for this wing is 2.5043 m*m.
After any wing-joining, our area is 2.50 m*m.
After any wing-joining, our semi-length is 7.01 m.
After any wing-joining, our root chord is 0.41 m.
After any wing-joining, our tip chord is 0.41 m.
After any wing-joining, our mean aero sweep is 0.1 deg.
After any wing-joining, our aspect ratio is 39.2491.
After any wing-joining, spanwise centroid is 0.5180 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.7407.
Finite-wing and build-up for prop 2: Wing area for this wing is 0.3368 m*m.
After any wing-joining, our area is 0.34 m*m.
After any wing-joining, our semi-length is 1.30 m.
After any wing-joining, our root chord is 0.29 m.
After any wing-joining, our tip chord is 0.29 m.
After any wing-joining, our mean aero sweep is 1.9 deg.
After any wing-joining, our aspect ratio is 9.9658.
After any wing-joining, spanwise centroid is 0.5511 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9245.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Vert Stab 2: Wing area for this wing is 1.1343 m*m.
After any wing-joining, our area is 1.13 m*m.
After any wing-joining, our semi-length is 1.89 m.
After any wing-joining, our root chord is 1.07 m.
After any wing-joining, our tip chord is 0.55 m.
After any wing-joining, our mean aero sweep is 42.0 deg.
After any wing-joining, our aspect ratio is 3.4774.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9783.
The prop 1 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.06, rad2= 0.70, ring area is 1.5404 m*m.
element number 1, rad1= 0.70, rad2= 1.40, ring area is 4.6238 m*m.
element number 2, rad1= 1.40, rad2= 2.10, ring area is 7.7198 m*m.
element number 3, rad1= 2.10, rad2= 2.80, ring area is 10.8077 m*m.
element number 4, rad1= 2.80, rad2= 3.51, ring area is 13.8956 m*m.
element number 5, rad1= 3.51, rad2= 4.21, ring area is 16.9835 m*m.
element number 6, rad1= 4.21, rad2= 4.91, ring area is 20.0714 m*m.
element number 7, rad1= 4.91, rad2= 5.61, ring area is 23.1594 m*m.
element number 8, rad1= 5.61, rad2= 6.31, ring area is 26.2481 m*m.
element number 9, rad1= 6.31, rad2= 7.01, ring area is 29.3425 m*m.
TOTAL DISC AREA=154.4039 m*m
en=0, el=0, element_mass= 6.774 veh_prop_ptr(en)->prop_mass=6.774,
rad_arm_mtr= 0.50, veh_prop_ptr(en)->prop_mi_rpm= 1.664 kg*m*m
en=0, el=1, element_mass= 19.432 veh_prop_ptr(en)->prop_mass=26.206,
rad_arm_mtr= 1.20, veh_prop_ptr(en)->prop_mi_rpm= 29.492 kg*m*m
en=0, el=2, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=59.518,
rad_arm_mtr= 1.90, veh_prop_ptr(en)->prop_mi_rpm=149.461 kg*m*m
en=0, el=3, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=92.831,
rad_arm_mtr= 2.60, veh_prop_ptr(en)->prop_mi_rpm=374.439 kg*m*m
en=0, el=4, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=126.144,
rad_arm_mtr= 3.30, veh_prop_ptr(en)->prop_mi_rpm=737.168 kg*m*m
en=0, el=5, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=159.456,
rad_arm_mtr= 4.00, veh_prop_ptr(en)->prop_mi_rpm=1270.392 kg*m*m
en=0, el=6, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=192.769,
rad_arm_mtr= 4.70, veh_prop_ptr(en)->prop_mi_rpm=2006.854 kg*m*m
en=0, el=7, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=226.081,
rad_arm_mtr= 5.40, veh_prop_ptr(en)->prop_mi_rpm=2979.298 kg*m*m
en=0, el=8, element_mass= 23.791 veh_prop_ptr(en)->prop_mass=249.873,
rad_arm_mtr= 6.10, veh_prop_ptr(en)->prop_mi_rpm=3865.719 kg*m*m
en=0, el=9, element_mass= 10.438 veh_prop_ptr(en)->prop_mass=260.310,
rad_arm_mtr= 6.80, veh_prop_ptr(en)->prop_mi_rpm=4349.075 kg*m*m
BEFORE any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The mass of prop 1 tip weights is 0.0 kg total (all blades) centered at
location 6.3 m
AFTER any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The prop 2 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.04, rad2= 0.14, ring area is 0.0574 m*m.
element number 1, rad1= 0.14, rad2= 0.26, ring area is 0.1474 m*m.
element number 2, rad1= 0.26, rad2= 0.39, ring area is 0.2636 m*m.
element number 3, rad1= 0.39, rad2= 0.52, ring area is 0.3690 m*m.
element number 4, rad1= 0.52, rad2= 0.65, ring area is 0.4745 m*m.
element number 5, rad1= 0.65, rad2= 0.78, ring area is 0.5799 m*m.
element number 6, rad1= 0.78, rad2= 0.91, ring area is 0.6853 m*m.
element number 7, rad1= 0.91, rad2= 1.04, ring area is 0.7908 m*m.
element number 8, rad1= 1.04, rad2= 1.17, ring area is 0.8962 m*m.
element number 9, rad1= 1.17, rad2= 1.30, ring area is 1.0016 m*m.
TOTAL DISC AREA= 5.2718 m*m
en=1, el=0, element_mass= 0.148 veh_prop_ptr(en)->prop_mass=0.148,
rad_arm_mtr= 0.09, veh_prop_ptr(en)->prop_mi_rpm= 0.001 kg*m*m
en=1, el=1, element_mass= 0.657 veh_prop_ptr(en)->prop_mass=0.806,
rad_arm_mtr= 0.22, veh_prop_ptr(en)->prop_mi_rpm= 0.033 kg*m*m
en=1, el=2, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=2.396,
rad_arm_mtr= 0.35, veh_prop_ptr(en)->prop_mi_rpm= 0.229 kg*m*m
en=1, el=3, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=3.986,
rad_arm_mtr= 0.48, veh_prop_ptr(en)->prop_mi_rpm= 0.596 kg*m*m
en=1, el=4, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=5.576,
rad_arm_mtr= 0.61, veh_prop_ptr(en)->prop_mi_rpm= 1.187 kg*m*m
en=1, el=5, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=7.166,
rad_arm_mtr= 0.74, veh_prop_ptr(en)->prop_mi_rpm= 2.056 kg*m*m
en=1, el=6, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=8.756,
rad_arm_mtr= 0.87, veh_prop_ptr(en)->prop_mi_rpm= 3.256 kg*m*m
en=1, el=7, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=10.346,
rad_arm_mtr= 1.00, veh_prop_ptr(en)->prop_mi_rpm= 4.841 kg*m*m
en=1, el=8, element_mass= 1.391 veh_prop_ptr(en)->prop_mass=11.737,
rad_arm_mtr= 1.13, veh_prop_ptr(en)->prop_mi_rpm= 6.611 kg*m*m
en=1, el=9, element_mass= 1.192 veh_prop_ptr(en)->prop_mass=12.929,
rad_arm_mtr= 1.26, veh_prop_ptr(en)->prop_mi_rpm= 8.496 kg*m*m
BEFORE any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
AFTER any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Engine # 0 is mass 248.206 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Engine # 1 is mass 248.206 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Prop # 0 is mass 260.310 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Prop # 1 is mass 12.929 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Fuel tank # 0 is mass 6.026 kg at x= 0.00, y= -0.06, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 1 is mass 3.515 kg at x= 0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 2 is mass 3.515 kg at x= -0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 3 is mass 10.545 kg at x= 0.00, y= -0.52, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 4 is mass 2.511 kg at x= 0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 5 is mass 2.511 kg at x= -0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 6 is mass 12.553 kg at x= 0.00, y= -0.98, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 7 is mass 4.519 kg at x= 0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Fuel tank # 8 is mass 4.519 kg at x= -0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Right Stab Running wetted area 0.3019 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Right Stab Running wetted area 0.6037 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Vert Stab 2 Running wetted area 0.9667 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.15 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 7.07 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 7.02 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Body 1 (fuselage):
The frontal area is 4.0966 m*m.
The side area is 14.3132 m*m.
The top area is 16.3570 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is 0.02 m.
The longitudinal centroid for lift at 0 slip is -3.85 m.
The longitudinal centroid for lift at 180 slip is 2.18 meters
Running wetted area 53.9898 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.98 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.11 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.09 m, based on mass-
distribution across the shell of the craft.
Body 22 (nacele):
The frontal area is 0.0188 m*m.
The side area is 0.1896 m*m.
The top area is 0.1911 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is 0.00 m.
The longitudinal centroid for lift at 180 slip is 0.61 meters
Running wetted area 54.6234 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.99 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.10 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.07 m, based on mass-
distribution across the shell of the craft.
Body 23 (hgiRaN tllec):
The frontal area is 0.0167 m*m.
The side area is 0.0849 m*m.
The top area is 0.0956 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is -0.46 m.
The longitudinal centroid for lift at 180 slip is -0.15 meters
Running wetted area 54.9388 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
Sum of all engines have mass of 496.41 kg ( 16% of total):
The radius of gyration of the engines in roll is 1.91 m, based on all
engine masses and locations.
The radius of gyration of the engines in pitch is 6.57 m, based on all
engine masses and locations.
The radius of gyration of the engines in yaw is 6.30 m, based on all
engine masses and locations.
Sum of all props have mass of 273.24 kg ( 9% of total):
The radius of gyration of the props in roll is 1.81 m, based on all prop
masses and locations.
The radius of gyration of the props in pitch is 2.65 m, based on all prop
masses and locations.
The radius of gyration of the props in yaw is 1.94 m, based on all prop
masses and locations.
Sum of all tanks have mass of 50.21 kg ( 2% of total):
The radius of gyration of the tanks in roll is 1.04 m, based on all tank
masses and locations.
The radius of gyration of the tanks in pitch is 1.08 m, based on all tank
masses and locations.
The radius of gyration of the tanks in yaw is 0.76 m, based on all tank
masses and locations.
Remainder of the craft has mass 2258.21 ( 73% of total):
The radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
As specified in the manual radius of gyration in the Weight and Balance screen in
Plane Maker:
The radius of gyration in roll is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
The radius of gyration in pitch is 4.07 m. (that's moment of inertia
50965.027 kg*m*m).
The radius of gyration in yaw is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
Wing area : 10.6907 m*m. (For wings 1 through 4 only, each times the
cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC : 0.26 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
Long-arm of 25% MAC : 0.00 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
X-Plane, by Austin Meyer
122103
Simulating Aircraft/Laminar Research/BELL 412 EPI/Bell412.acf
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
x location positive aft x force positive right pitch/alpha pos nose up
y location positive right y force positive up roll pos right
z location positive up z force positive aft yaw/beta pos nose right
elevator, aileron, spoiler positive control surface up
rudder positive control surface right
drag-yaw positive control surface deployed
pitch cyclic prop pitch positive request nose up
roll cyclic prop pitch positive request nose right
Finite-wing and build-up for prop 1: Wing area for this wing is 2.5043 m*m.
After any wing-joining, our area is 2.50 m*m.
After any wing-joining, our semi-length is 7.01 m.
After any wing-joining, our root chord is 0.41 m.
After any wing-joining, our tip chord is 0.41 m.
After any wing-joining, our mean aero sweep is 0.1 deg.
After any wing-joining, our aspect ratio is 39.2491.
After any wing-joining, spanwise centroid is 0.5180 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.7407.
Finite-wing and build-up for prop 2: Wing area for this wing is 0.3368 m*m.
After any wing-joining, our area is 0.34 m*m.
After any wing-joining, our semi-length is 1.30 m.
After any wing-joining, our root chord is 0.29 m.
After any wing-joining, our tip chord is 0.29 m.
After any wing-joining, our mean aero sweep is 1.9 deg.
After any wing-joining, our aspect ratio is 9.9658.
After any wing-joining, spanwise centroid is 0.5511 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9245.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Vert Stab 2: Wing area for this wing is 1.1343 m*m.
After any wing-joining, our area is 1.13 m*m.
After any wing-joining, our semi-length is 1.89 m.
After any wing-joining, our root chord is 1.07 m.
After any wing-joining, our tip chord is 0.55 m.
After any wing-joining, our mean aero sweep is 42.0 deg.
After any wing-joining, our aspect ratio is 3.4774.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9783.
The prop 1 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.06, rad2= 0.70, ring area is 1.5404 m*m.
element number 1, rad1= 0.70, rad2= 1.40, ring area is 4.6238 m*m.
element number 2, rad1= 1.40, rad2= 2.10, ring area is 7.7198 m*m.
element number 3, rad1= 2.10, rad2= 2.80, ring area is 10.8077 m*m.
element number 4, rad1= 2.80, rad2= 3.51, ring area is 13.8956 m*m.
element number 5, rad1= 3.51, rad2= 4.21, ring area is 16.9835 m*m.
element number 6, rad1= 4.21, rad2= 4.91, ring area is 20.0714 m*m.
element number 7, rad1= 4.91, rad2= 5.61, ring area is 23.1594 m*m.
element number 8, rad1= 5.61, rad2= 6.31, ring area is 26.2481 m*m.
element number 9, rad1= 6.31, rad2= 7.01, ring area is 29.3425 m*m.
TOTAL DISC AREA=154.4039 m*m
en=0, el=0, element_mass= 6.774 veh_prop_ptr(en)->prop_mass=6.774,
rad_arm_mtr= 0.50, veh_prop_ptr(en)->prop_mi_rpm= 1.664 kg*m*m
en=0, el=1, element_mass= 19.432 veh_prop_ptr(en)->prop_mass=26.206,
rad_arm_mtr= 1.20, veh_prop_ptr(en)->prop_mi_rpm= 29.492 kg*m*m
en=0, el=2, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=59.518,
rad_arm_mtr= 1.90, veh_prop_ptr(en)->prop_mi_rpm=149.461 kg*m*m
en=0, el=3, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=92.831,
rad_arm_mtr= 2.60, veh_prop_ptr(en)->prop_mi_rpm=374.439 kg*m*m
en=0, el=4, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=126.144,
rad_arm_mtr= 3.30, veh_prop_ptr(en)->prop_mi_rpm=737.168 kg*m*m
en=0, el=5, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=159.456,
rad_arm_mtr= 4.00, veh_prop_ptr(en)->prop_mi_rpm=1270.392 kg*m*m
en=0, el=6, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=192.769,
rad_arm_mtr= 4.70, veh_prop_ptr(en)->prop_mi_rpm=2006.854 kg*m*m
en=0, el=7, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=226.081,
rad_arm_mtr= 5.40, veh_prop_ptr(en)->prop_mi_rpm=2979.298 kg*m*m
en=0, el=8, element_mass= 23.791 veh_prop_ptr(en)->prop_mass=249.873,
rad_arm_mtr= 6.10, veh_prop_ptr(en)->prop_mi_rpm=3865.719 kg*m*m
en=0, el=9, element_mass= 10.438 veh_prop_ptr(en)->prop_mass=260.310,
rad_arm_mtr= 6.80, veh_prop_ptr(en)->prop_mi_rpm=4349.075 kg*m*m
BEFORE any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The mass of prop 1 tip weights is 0.0 kg total (all blades) centered at
location 6.3 m
AFTER any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The prop 2 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.04, rad2= 0.14, ring area is 0.0574 m*m.
element number 1, rad1= 0.14, rad2= 0.26, ring area is 0.1474 m*m.
element number 2, rad1= 0.26, rad2= 0.39, ring area is 0.2636 m*m.
element number 3, rad1= 0.39, rad2= 0.52, ring area is 0.3690 m*m.
element number 4, rad1= 0.52, rad2= 0.65, ring area is 0.4745 m*m.
element number 5, rad1= 0.65, rad2= 0.78, ring area is 0.5799 m*m.
element number 6, rad1= 0.78, rad2= 0.91, ring area is 0.6853 m*m.
element number 7, rad1= 0.91, rad2= 1.04, ring area is 0.7908 m*m.
element number 8, rad1= 1.04, rad2= 1.17, ring area is 0.8962 m*m.
element number 9, rad1= 1.17, rad2= 1.30, ring area is 1.0016 m*m.
TOTAL DISC AREA= 5.2718 m*m
en=1, el=0, element_mass= 0.148 veh_prop_ptr(en)->prop_mass=0.148,
rad_arm_mtr= 0.09, veh_prop_ptr(en)->prop_mi_rpm= 0.001 kg*m*m
en=1, el=1, element_mass= 0.657 veh_prop_ptr(en)->prop_mass=0.806,
rad_arm_mtr= 0.22, veh_prop_ptr(en)->prop_mi_rpm= 0.033 kg*m*m
en=1, el=2, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=2.396,
rad_arm_mtr= 0.35, veh_prop_ptr(en)->prop_mi_rpm= 0.229 kg*m*m
en=1, el=3, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=3.986,
rad_arm_mtr= 0.48, veh_prop_ptr(en)->prop_mi_rpm= 0.596 kg*m*m
en=1, el=4, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=5.576,
rad_arm_mtr= 0.61, veh_prop_ptr(en)->prop_mi_rpm= 1.187 kg*m*m
en=1, el=5, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=7.166,
rad_arm_mtr= 0.74, veh_prop_ptr(en)->prop_mi_rpm= 2.056 kg*m*m
en=1, el=6, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=8.756,
rad_arm_mtr= 0.87, veh_prop_ptr(en)->prop_mi_rpm= 3.256 kg*m*m
en=1, el=7, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=10.346,
rad_arm_mtr= 1.00, veh_prop_ptr(en)->prop_mi_rpm= 4.841 kg*m*m
en=1, el=8, element_mass= 1.391 veh_prop_ptr(en)->prop_mass=11.737,
rad_arm_mtr= 1.13, veh_prop_ptr(en)->prop_mi_rpm= 6.611 kg*m*m
en=1, el=9, element_mass= 1.192 veh_prop_ptr(en)->prop_mass=12.929,
rad_arm_mtr= 1.26, veh_prop_ptr(en)->prop_mi_rpm= 8.496 kg*m*m
BEFORE any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
AFTER any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Engine # 0 is mass 248.206 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Engine # 1 is mass 248.206 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Prop # 0 is mass 260.310 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Prop # 1 is mass 12.929 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Fuel tank # 0 is mass 6.026 kg at x= 0.00, y= -0.06, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 1 is mass 3.515 kg at x= 0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 2 is mass 3.515 kg at x= -0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 3 is mass 10.545 kg at x= 0.00, y= -0.52, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 4 is mass 2.511 kg at x= 0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 5 is mass 2.511 kg at x= -0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 6 is mass 12.553 kg at x= 0.00, y= -0.98, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 7 is mass 4.519 kg at x= 0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Fuel tank # 8 is mass 4.519 kg at x= -0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Right Stab Running wetted area 0.3019 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Right Stab Running wetted area 0.6037 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Vert Stab 2 Running wetted area 0.9667 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.15 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 7.07 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 7.02 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Body 1 (fuselage):
The frontal area is 4.0966 m*m.
The side area is 14.3132 m*m.
The top area is 16.3570 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is 0.02 m.
The longitudinal centroid for lift at 0 slip is -3.85 m.
The longitudinal centroid for lift at 180 slip is 2.18 meters
Running wetted area 53.9898 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.98 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.11 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.09 m, based on mass-
distribution across the shell of the craft.
Body 22 (nacele):
The frontal area is 0.0188 m*m.
The side area is 0.1896 m*m.
The top area is 0.1911 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is 0.00 m.
The longitudinal centroid for lift at 180 slip is 0.61 meters
Running wetted area 54.6234 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.99 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.10 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.07 m, based on mass-
distribution across the shell of the craft.
Body 23 (hgiRaN tllec):
The frontal area is 0.0167 m*m.
The side area is 0.0849 m*m.
The top area is 0.0956 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is -0.46 m.
The longitudinal centroid for lift at 180 slip is -0.15 meters
Running wetted area 54.9388 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
Sum of all engines have mass of 496.41 kg ( 16% of total):
The radius of gyration of the engines in roll is 1.91 m, based on all
engine masses and locations.
The radius of gyration of the engines in pitch is 6.57 m, based on all
engine masses and locations.
The radius of gyration of the engines in yaw is 6.30 m, based on all
engine masses and locations.
Sum of all props have mass of 273.24 kg ( 9% of total):
The radius of gyration of the props in roll is 1.81 m, based on all prop
masses and locations.
The radius of gyration of the props in pitch is 2.65 m, based on all prop
masses and locations.
The radius of gyration of the props in yaw is 1.94 m, based on all prop
masses and locations.
Sum of all tanks have mass of 50.21 kg ( 2% of total):
The radius of gyration of the tanks in roll is 1.04 m, based on all tank
masses and locations.
The radius of gyration of the tanks in pitch is 1.08 m, based on all tank
masses and locations.
The radius of gyration of the tanks in yaw is 0.76 m, based on all tank
masses and locations.
Remainder of the craft has mass 2258.21 ( 73% of total):
The radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
As specified in the manual radius of gyration in the Weight and Balance screen in
Plane Maker:
The radius of gyration in roll is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
The radius of gyration in pitch is 4.07 m. (that's moment of inertia
50965.027 kg*m*m).
The radius of gyration in yaw is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
Wing area : 10.6907 m*m. (For wings 1 through 4 only, each times the
cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC : 0.26 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
Long-arm of 25% MAC : 0.00 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
X-Plane, by Austin Meyer
122103
Simulating Aircraft/Laminar Research/BELL 412 EPI/Bell412.acf
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
x location positive aft x force positive right pitch/alpha pos nose up
y location positive right y force positive up roll pos right
z location positive up z force positive aft yaw/beta pos nose right
elevator, aileron, spoiler positive control surface up
rudder positive control surface right
drag-yaw positive control surface deployed
pitch cyclic prop pitch positive request nose up
roll cyclic prop pitch positive request nose right
Finite-wing and build-up for prop 1: Wing area for this wing is 2.5043 m*m.
After any wing-joining, our area is 2.50 m*m.
After any wing-joining, our semi-length is 7.01 m.
After any wing-joining, our root chord is 0.41 m.
After any wing-joining, our tip chord is 0.41 m.
After any wing-joining, our mean aero sweep is 0.1 deg.
After any wing-joining, our aspect ratio is 39.2491.
After any wing-joining, spanwise centroid is 0.5180 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.7407.
Finite-wing and build-up for prop 2: Wing area for this wing is 0.3368 m*m.
After any wing-joining, our area is 0.34 m*m.
After any wing-joining, our semi-length is 1.30 m.
After any wing-joining, our root chord is 0.29 m.
After any wing-joining, our tip chord is 0.29 m.
After any wing-joining, our mean aero sweep is 1.9 deg.
After any wing-joining, our aspect ratio is 9.9658.
After any wing-joining, spanwise centroid is 0.5511 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9245.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Vert Stab 2: Wing area for this wing is 1.1343 m*m.
After any wing-joining, our area is 1.13 m*m.
After any wing-joining, our semi-length is 1.89 m.
After any wing-joining, our root chord is 1.07 m.
After any wing-joining, our tip chord is 0.55 m.
After any wing-joining, our mean aero sweep is 42.0 deg.
After any wing-joining, our aspect ratio is 3.4774.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9783.
The prop 1 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.06, rad2= 0.70, ring area is 1.5404 m*m.
element number 1, rad1= 0.70, rad2= 1.40, ring area is 4.6238 m*m.
element number 2, rad1= 1.40, rad2= 2.10, ring area is 7.7198 m*m.
element number 3, rad1= 2.10, rad2= 2.80, ring area is 10.8077 m*m.
element number 4, rad1= 2.80, rad2= 3.51, ring area is 13.8956 m*m.
element number 5, rad1= 3.51, rad2= 4.21, ring area is 16.9835 m*m.
element number 6, rad1= 4.21, rad2= 4.91, ring area is 20.0714 m*m.
element number 7, rad1= 4.91, rad2= 5.61, ring area is 23.1594 m*m.
element number 8, rad1= 5.61, rad2= 6.31, ring area is 26.2481 m*m.
element number 9, rad1= 6.31, rad2= 7.01, ring area is 29.3425 m*m.
TOTAL DISC AREA=154.4039 m*m
en=0, el=0, element_mass= 6.774 veh_prop_ptr(en)->prop_mass=6.774,
rad_arm_mtr= 0.50, veh_prop_ptr(en)->prop_mi_rpm= 1.664 kg*m*m
en=0, el=1, element_mass= 19.432 veh_prop_ptr(en)->prop_mass=26.206,
rad_arm_mtr= 1.20, veh_prop_ptr(en)->prop_mi_rpm= 29.492 kg*m*m
en=0, el=2, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=59.518,
rad_arm_mtr= 1.90, veh_prop_ptr(en)->prop_mi_rpm=149.461 kg*m*m
en=0, el=3, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=92.831,
rad_arm_mtr= 2.60, veh_prop_ptr(en)->prop_mi_rpm=374.439 kg*m*m
en=0, el=4, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=126.144,
rad_arm_mtr= 3.30, veh_prop_ptr(en)->prop_mi_rpm=737.168 kg*m*m
en=0, el=5, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=159.456,
rad_arm_mtr= 4.00, veh_prop_ptr(en)->prop_mi_rpm=1270.392 kg*m*m
en=0, el=6, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=192.769,
rad_arm_mtr= 4.70, veh_prop_ptr(en)->prop_mi_rpm=2006.854 kg*m*m
en=0, el=7, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=226.081,
rad_arm_mtr= 5.40, veh_prop_ptr(en)->prop_mi_rpm=2979.298 kg*m*m
en=0, el=8, element_mass= 23.791 veh_prop_ptr(en)->prop_mass=249.873,
rad_arm_mtr= 6.10, veh_prop_ptr(en)->prop_mi_rpm=3865.719 kg*m*m
en=0, el=9, element_mass= 10.438 veh_prop_ptr(en)->prop_mass=260.310,
rad_arm_mtr= 6.80, veh_prop_ptr(en)->prop_mi_rpm=4349.075 kg*m*m
BEFORE any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The mass of prop 1 tip weights is 0.0 kg total (all blades) centered at
location 6.3 m
AFTER any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The prop 2 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.04, rad2= 0.14, ring area is 0.0574 m*m.
element number 1, rad1= 0.14, rad2= 0.26, ring area is 0.1474 m*m.
element number 2, rad1= 0.26, rad2= 0.39, ring area is 0.2636 m*m.
element number 3, rad1= 0.39, rad2= 0.52, ring area is 0.3690 m*m.
element number 4, rad1= 0.52, rad2= 0.65, ring area is 0.4745 m*m.
element number 5, rad1= 0.65, rad2= 0.78, ring area is 0.5799 m*m.
element number 6, rad1= 0.78, rad2= 0.91, ring area is 0.6853 m*m.
element number 7, rad1= 0.91, rad2= 1.04, ring area is 0.7908 m*m.
element number 8, rad1= 1.04, rad2= 1.17, ring area is 0.8962 m*m.
element number 9, rad1= 1.17, rad2= 1.30, ring area is 1.0016 m*m.
TOTAL DISC AREA= 5.2718 m*m
en=1, el=0, element_mass= 0.148 veh_prop_ptr(en)->prop_mass=0.148,
rad_arm_mtr= 0.09, veh_prop_ptr(en)->prop_mi_rpm= 0.001 kg*m*m
en=1, el=1, element_mass= 0.657 veh_prop_ptr(en)->prop_mass=0.806,
rad_arm_mtr= 0.22, veh_prop_ptr(en)->prop_mi_rpm= 0.033 kg*m*m
en=1, el=2, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=2.396,
rad_arm_mtr= 0.35, veh_prop_ptr(en)->prop_mi_rpm= 0.229 kg*m*m
en=1, el=3, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=3.986,
rad_arm_mtr= 0.48, veh_prop_ptr(en)->prop_mi_rpm= 0.596 kg*m*m
en=1, el=4, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=5.576,
rad_arm_mtr= 0.61, veh_prop_ptr(en)->prop_mi_rpm= 1.187 kg*m*m
en=1, el=5, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=7.166,
rad_arm_mtr= 0.74, veh_prop_ptr(en)->prop_mi_rpm= 2.056 kg*m*m
en=1, el=6, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=8.756,
rad_arm_mtr= 0.87, veh_prop_ptr(en)->prop_mi_rpm= 3.256 kg*m*m
en=1, el=7, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=10.346,
rad_arm_mtr= 1.00, veh_prop_ptr(en)->prop_mi_rpm= 4.841 kg*m*m
en=1, el=8, element_mass= 1.391 veh_prop_ptr(en)->prop_mass=11.737,
rad_arm_mtr= 1.13, veh_prop_ptr(en)->prop_mi_rpm= 6.611 kg*m*m
en=1, el=9, element_mass= 1.192 veh_prop_ptr(en)->prop_mass=12.929,
rad_arm_mtr= 1.26, veh_prop_ptr(en)->prop_mi_rpm= 8.496 kg*m*m
BEFORE any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
AFTER any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Engine # 0 is mass 248.206 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Engine # 1 is mass 248.206 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Prop # 0 is mass 260.310 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Prop # 1 is mass 12.929 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Fuel tank # 0 is mass 6.026 kg at x= 0.00, y= -0.06, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 1 is mass 3.515 kg at x= 0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 2 is mass 3.515 kg at x= -0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 3 is mass 10.545 kg at x= 0.00, y= -0.52, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 4 is mass 2.511 kg at x= 0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 5 is mass 2.511 kg at x= -0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 6 is mass 12.553 kg at x= 0.00, y= -0.98, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 7 is mass 4.519 kg at x= 0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Fuel tank # 8 is mass 4.519 kg at x= -0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Right Stab Running wetted area 0.3019 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Right Stab Running wetted area 0.6037 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Vert Stab 2 Running wetted area 0.9667 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.15 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 7.07 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 7.02 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Body 1 (fuselage):
The frontal area is 4.0966 m*m.
The side area is 14.3132 m*m.
The top area is 16.3570 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is 0.02 m.
The longitudinal centroid for lift at 0 slip is -3.85 m.
The longitudinal centroid for lift at 180 slip is 2.18 meters
Running wetted area 53.9898 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.98 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.11 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.09 m, based on mass-
distribution across the shell of the craft.
Body 22 (nacele):
The frontal area is 0.0188 m*m.
The side area is 0.1896 m*m.
The top area is 0.1911 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is 0.00 m.
The longitudinal centroid for lift at 180 slip is 0.61 meters
Running wetted area 54.6234 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.99 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.10 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.07 m, based on mass-
distribution across the shell of the craft.
Body 23 (hgiRaN tllec):
The frontal area is 0.0167 m*m.
The side area is 0.0849 m*m.
The top area is 0.0956 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is -0.46 m.
The longitudinal centroid for lift at 180 slip is -0.15 meters
Running wetted area 54.9388 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
Sum of all engines have mass of 496.41 kg ( 16% of total):
The radius of gyration of the engines in roll is 1.91 m, based on all
engine masses and locations.
The radius of gyration of the engines in pitch is 6.57 m, based on all
engine masses and locations.
The radius of gyration of the engines in yaw is 6.30 m, based on all
engine masses and locations.
Sum of all props have mass of 273.24 kg ( 9% of total):
The radius of gyration of the props in roll is 1.81 m, based on all prop
masses and locations.
The radius of gyration of the props in pitch is 2.65 m, based on all prop
masses and locations.
The radius of gyration of the props in yaw is 1.94 m, based on all prop
masses and locations.
Sum of all tanks have mass of 50.21 kg ( 2% of total):
The radius of gyration of the tanks in roll is 1.04 m, based on all tank
masses and locations.
The radius of gyration of the tanks in pitch is 1.08 m, based on all tank
masses and locations.
The radius of gyration of the tanks in yaw is 0.76 m, based on all tank
masses and locations.
Remainder of the craft has mass 2258.21 ( 73% of total):
The radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
As specified in the manual radius of gyration in the Weight and Balance screen in
Plane Maker:
The radius of gyration in roll is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
The radius of gyration in pitch is 4.07 m. (that's moment of inertia
50965.027 kg*m*m).
The radius of gyration in yaw is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
Wing area : 10.6907 m*m. (For wings 1 through 4 only, each times the
cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC : 0.26 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
Long-arm of 25% MAC : 0.00 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
X-Plane, by Austin Meyer
122103
Simulating Aircraft/Laminar Research/BELL 412 EPI/Bell412.acf
•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
•••••••••••••••••
x location positive aft x force positive right pitch/alpha pos nose up
y location positive right y force positive up roll pos right
z location positive up z force positive aft yaw/beta pos nose right
elevator, aileron, spoiler positive control surface up
rudder positive control surface right
drag-yaw positive control surface deployed
pitch cyclic prop pitch positive request nose up
roll cyclic prop pitch positive request nose right
Finite-wing and build-up for prop 1: Wing area for this wing is 2.5043 m*m.
After any wing-joining, our area is 2.50 m*m.
After any wing-joining, our semi-length is 7.01 m.
After any wing-joining, our root chord is 0.41 m.
After any wing-joining, our tip chord is 0.41 m.
After any wing-joining, our mean aero sweep is 0.1 deg.
After any wing-joining, our aspect ratio is 39.2491.
After any wing-joining, spanwise centroid is 0.5180 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.7407.
Finite-wing and build-up for prop 2: Wing area for this wing is 0.3368 m*m.
After any wing-joining, our area is 0.34 m*m.
After any wing-joining, our semi-length is 1.30 m.
After any wing-joining, our root chord is 0.29 m.
After any wing-joining, our tip chord is 0.29 m.
After any wing-joining, our mean aero sweep is 1.9 deg.
After any wing-joining, our aspect ratio is 9.9658.
After any wing-joining, spanwise centroid is 0.5511 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9245.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Right Stab: Wing area for this wing is 0.9523 m*m.
After any wing-joining, our area is 0.95 m*m.
After any wing-joining, our semi-length is 1.25 m.
After any wing-joining, our root chord is 0.76 m.
After any wing-joining, our tip chord is 0.76 m.
After any wing-joining, our mean aero sweep is 0.0 deg.
After any wing-joining, our aspect ratio is 3.2800.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9800.
Finite-wing and build-up for Vert Stab 2: Wing area for this wing is 1.1343 m*m.
After any wing-joining, our area is 1.13 m*m.
After any wing-joining, our semi-length is 1.89 m.
After any wing-joining, our root chord is 1.07 m.
After any wing-joining, our tip chord is 0.55 m.
After any wing-joining, our mean aero sweep is 42.0 deg.
After any wing-joining, our aspect ratio is 3.4774.
After any wing-joining, spanwise centroid is 0.5000 semi-spans. (this is
area centroid fraction of the way out to the tip)
After any wing-joining, our taper ratio is 1.0000.
Oswalds efficiency is therefore 0.9783.
The prop 1 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.06, rad2= 0.70, ring area is 1.5404 m*m.
element number 1, rad1= 0.70, rad2= 1.40, ring area is 4.6238 m*m.
element number 2, rad1= 1.40, rad2= 2.10, ring area is 7.7198 m*m.
element number 3, rad1= 2.10, rad2= 2.80, ring area is 10.8077 m*m.
element number 4, rad1= 2.80, rad2= 3.51, ring area is 13.8956 m*m.
element number 5, rad1= 3.51, rad2= 4.21, ring area is 16.9835 m*m.
element number 6, rad1= 4.21, rad2= 4.91, ring area is 20.0714 m*m.
element number 7, rad1= 4.91, rad2= 5.61, ring area is 23.1594 m*m.
element number 8, rad1= 5.61, rad2= 6.31, ring area is 26.2481 m*m.
element number 9, rad1= 6.31, rad2= 7.01, ring area is 29.3425 m*m.
TOTAL DISC AREA=154.4039 m*m
en=0, el=0, element_mass= 6.774 veh_prop_ptr(en)->prop_mass=6.774,
rad_arm_mtr= 0.50, veh_prop_ptr(en)->prop_mi_rpm= 1.664 kg*m*m
en=0, el=1, element_mass= 19.432 veh_prop_ptr(en)->prop_mass=26.206,
rad_arm_mtr= 1.20, veh_prop_ptr(en)->prop_mi_rpm= 29.492 kg*m*m
en=0, el=2, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=59.518,
rad_arm_mtr= 1.90, veh_prop_ptr(en)->prop_mi_rpm=149.461 kg*m*m
en=0, el=3, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=92.831,
rad_arm_mtr= 2.60, veh_prop_ptr(en)->prop_mi_rpm=374.439 kg*m*m
en=0, el=4, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=126.144,
rad_arm_mtr= 3.30, veh_prop_ptr(en)->prop_mi_rpm=737.168 kg*m*m
en=0, el=5, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=159.456,
rad_arm_mtr= 4.00, veh_prop_ptr(en)->prop_mi_rpm=1270.392 kg*m*m
en=0, el=6, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=192.769,
rad_arm_mtr= 4.70, veh_prop_ptr(en)->prop_mi_rpm=2006.854 kg*m*m
en=0, el=7, element_mass= 33.313 veh_prop_ptr(en)->prop_mass=226.081,
rad_arm_mtr= 5.40, veh_prop_ptr(en)->prop_mi_rpm=2979.298 kg*m*m
en=0, el=8, element_mass= 23.791 veh_prop_ptr(en)->prop_mass=249.873,
rad_arm_mtr= 6.10, veh_prop_ptr(en)->prop_mi_rpm=3865.719 kg*m*m
en=0, el=9, element_mass= 10.438 veh_prop_ptr(en)->prop_mass=260.310,
rad_arm_mtr= 6.80, veh_prop_ptr(en)->prop_mi_rpm=4349.075 kg*m*m
BEFORE any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The mass of prop 1 tip weights is 0.0 kg total (all blades) centered at
location 6.3 m
AFTER any tip weights, the prop 1 weighs 260.310 kg, and the MI is 4349.075
kg*m*m
The prop 2 DISC AREA is broken down into rings for propwash distribution as
follows:
element number 0, rad1= 0.04, rad2= 0.14, ring area is 0.0574 m*m.
element number 1, rad1= 0.14, rad2= 0.26, ring area is 0.1474 m*m.
element number 2, rad1= 0.26, rad2= 0.39, ring area is 0.2636 m*m.
element number 3, rad1= 0.39, rad2= 0.52, ring area is 0.3690 m*m.
element number 4, rad1= 0.52, rad2= 0.65, ring area is 0.4745 m*m.
element number 5, rad1= 0.65, rad2= 0.78, ring area is 0.5799 m*m.
element number 6, rad1= 0.78, rad2= 0.91, ring area is 0.6853 m*m.
element number 7, rad1= 0.91, rad2= 1.04, ring area is 0.7908 m*m.
element number 8, rad1= 1.04, rad2= 1.17, ring area is 0.8962 m*m.
element number 9, rad1= 1.17, rad2= 1.30, ring area is 1.0016 m*m.
TOTAL DISC AREA= 5.2718 m*m
en=1, el=0, element_mass= 0.148 veh_prop_ptr(en)->prop_mass=0.148,
rad_arm_mtr= 0.09, veh_prop_ptr(en)->prop_mi_rpm= 0.001 kg*m*m
en=1, el=1, element_mass= 0.657 veh_prop_ptr(en)->prop_mass=0.806,
rad_arm_mtr= 0.22, veh_prop_ptr(en)->prop_mi_rpm= 0.033 kg*m*m
en=1, el=2, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=2.396,
rad_arm_mtr= 0.35, veh_prop_ptr(en)->prop_mi_rpm= 0.229 kg*m*m
en=1, el=3, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=3.986,
rad_arm_mtr= 0.48, veh_prop_ptr(en)->prop_mi_rpm= 0.596 kg*m*m
en=1, el=4, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=5.576,
rad_arm_mtr= 0.61, veh_prop_ptr(en)->prop_mi_rpm= 1.187 kg*m*m
en=1, el=5, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=7.166,
rad_arm_mtr= 0.74, veh_prop_ptr(en)->prop_mi_rpm= 2.056 kg*m*m
en=1, el=6, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=8.756,
rad_arm_mtr= 0.87, veh_prop_ptr(en)->prop_mi_rpm= 3.256 kg*m*m
en=1, el=7, element_mass= 1.590 veh_prop_ptr(en)->prop_mass=10.346,
rad_arm_mtr= 1.00, veh_prop_ptr(en)->prop_mi_rpm= 4.841 kg*m*m
en=1, el=8, element_mass= 1.391 veh_prop_ptr(en)->prop_mass=11.737,
rad_arm_mtr= 1.13, veh_prop_ptr(en)->prop_mi_rpm= 6.611 kg*m*m
en=1, el=9, element_mass= 1.192 veh_prop_ptr(en)->prop_mass=12.929,
rad_arm_mtr= 1.26, veh_prop_ptr(en)->prop_mi_rpm= 8.496 kg*m*m
BEFORE any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
AFTER any tip weights, the prop 2 weighs 12.929 kg, and the MI is 8.496
kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Critical altitude for prop engines= 0 ft, rho at crit alt= 1.2250 kg/mmm, rho at
SL= 1.2250 kg/mmm, engine power boosted to 1.0000 of original, spinning motor MI
1.7529 kg*m*m
Engine # 0 is mass 248.206 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Engine # 1 is mass 248.206 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Prop # 0 is mass 260.310 kg at x= 0.00, y= 1.80, z= -0.04 (for moment of
inertia build-up)
Prop # 1 is mass 12.929 kg at x= 0.40, y= 1.97, z= 8.90 (for moment of
inertia build-up)
Fuel tank # 0 is mass 6.026 kg at x= 0.00, y= -0.06, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 1 is mass 3.515 kg at x= 0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 2 is mass 3.515 kg at x= -0.76, y= -1.13, z= -0.30 (for moment
of inertia build-up)
Fuel tank # 3 is mass 10.545 kg at x= 0.00, y= -0.52, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 4 is mass 2.511 kg at x= 0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 5 is mass 2.511 kg at x= -0.76, y= -1.13, z= -0.91 (for moment
of inertia build-up)
Fuel tank # 6 is mass 12.553 kg at x= 0.00, y= -0.98, z= 0.61 (for moment
of inertia build-up)
Fuel tank # 7 is mass 4.519 kg at x= 0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Fuel tank # 8 is mass 4.519 kg at x= -0.76, y= -1.13, z= 0.30 (for moment
of inertia build-up)
Right Stab Running wetted area 0.3019 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Right Stab Running wetted area 0.6037 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.77 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 5.88 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 5.93 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Vert Stab 2 Running wetted area 0.9667 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.15 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in pitch is 7.07 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Running radius of gyration of the shell in yaw is 7.02 m, based on mass-
distribution across the shell of the craft with the 0.12 thickness wing giving a
0.16 weighting per square meter on this flying surface.
Body 1 (fuselage):
The frontal area is 4.0966 m*m.
The side area is 14.3132 m*m.
The top area is 16.3570 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is 0.02 m.
The longitudinal centroid for lift at 0 slip is -3.85 m.
The longitudinal centroid for lift at 180 slip is 2.18 meters
Running wetted area 53.9898 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.98 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.11 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.09 m, based on mass-
distribution across the shell of the craft.
Body 22 (nacele):
The frontal area is 0.0188 m*m.
The side area is 0.1896 m*m.
The top area is 0.1911 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is 0.00 m.
The longitudinal centroid for lift at 180 slip is 0.61 meters
Running wetted area 54.6234 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 0.99 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.10 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.07 m, based on mass-
distribution across the shell of the craft.
Body 23 (hgiRaN tllec):
The frontal area is 0.0167 m*m.
The side area is 0.0849 m*m.
The top area is 0.0956 m*m.
The lateral centroid is 0.00 m.
The vertical centroid is -0.00 m.
The longitudinal centroid for lift at 0 slip is -0.46 m.
The longitudinal centroid for lift at 180 slip is -0.15 meters
Running wetted area 54.9388 square meters for all parts listed so far
Running radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
Running radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
Sum of all engines have mass of 496.41 kg ( 16% of total):
The radius of gyration of the engines in roll is 1.91 m, based on all
engine masses and locations.
The radius of gyration of the engines in pitch is 6.57 m, based on all
engine masses and locations.
The radius of gyration of the engines in yaw is 6.30 m, based on all
engine masses and locations.
Sum of all props have mass of 273.24 kg ( 9% of total):
The radius of gyration of the props in roll is 1.81 m, based on all prop
masses and locations.
The radius of gyration of the props in pitch is 2.65 m, based on all prop
masses and locations.
The radius of gyration of the props in yaw is 1.94 m, based on all prop
masses and locations.
Sum of all tanks have mass of 50.21 kg ( 2% of total):
The radius of gyration of the tanks in roll is 1.04 m, based on all tank
masses and locations.
The radius of gyration of the tanks in pitch is 1.08 m, based on all tank
masses and locations.
The radius of gyration of the tanks in yaw is 0.76 m, based on all tank
masses and locations.
Remainder of the craft has mass 2258.21 ( 73% of total):
The radius of gyration of the shell in roll is 1.00 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in pitch is 3.16 m, based on mass-
distribution across the shell of the craft.
The radius of gyration of the shell in yaw is 3.13 m, based on mass-
distribution across the shell of the craft.
As specified in the manual radius of gyration in the Weight and Balance screen in
Plane Maker:
The radius of gyration in roll is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
The radius of gyration in pitch is 4.07 m. (that's moment of inertia
50965.027 kg*m*m).
The radius of gyration in yaw is 2.48 m. (that's moment of inertia
18994.369 kg*m*m).
Wing area : 10.6907 m*m. (For wings 1 through 4 only, each times the
cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC : 0.26 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
Long-arm of 25% MAC : 0.00 m. (For wings 1 through 4 only! This does not
include stabilizers or misc wings!)
You might also like
- Structural Optimization and Weight Reduction of Spar and Ribs IJERTV7IS040349No ratings yetStructural Optimization and Weight Reduction of Spar and Ribs IJERTV7IS0403496 pages
- Design Study On Low Drag Low Aspect Ratio Wing For Racecar Application Monza 2021No ratings yetDesign Study On Low Drag Low Aspect Ratio Wing For Racecar Application Monza 202167 pages
- Aircraft Design Project-2 Eight Seater Short Range Business Jet Aircraft79% (14)Aircraft Design Project-2 Eight Seater Short Range Business Jet Aircraft69 pages
- Veltech Rangarajan DR - Sagunthala R&D Institute of Science and TechnologyNo ratings yetVeltech Rangarajan DR - Sagunthala R&D Institute of Science and Technology30 pages
- Calculation of Aircraft Aerodynamic Characteristics (Sem6)No ratings yetCalculation of Aircraft Aerodynamic Characteristics (Sem6)10 pages
- March I I, 192©: 1 2 ." O-Io O-2Q 0 - 1020No ratings yetMarch I I, 192©: 1 2 ." O-Io O-2Q 0 - 10201 page
- SubsonicAircraftWingConceptualDesign-SynthesisandAnalysis IJSBARNo ratings yetSubsonicAircraftWingConceptualDesign-SynthesisandAnalysis IJSBAR44 pages
- Aeroelastic Flight Control For Subscale Uavs: April 2007No ratings yetAeroelastic Flight Control For Subscale Uavs: April 200713 pages
- Rcplaneandaerofoildesignbst Caculations2 1 11 230116110353 031ea382No ratings yetRcplaneandaerofoildesignbst Caculations2 1 11 230116110353 031ea38254 pages
- Aerodynamic Design Studies of Conventional & Unconventional Wings With WingletsNo ratings yetAerodynamic Design Studies of Conventional & Unconventional Wings With Winglets18 pages
- Fly High - Technical Report No. 8 Aircraft Layout DataNo ratings yetFly High - Technical Report No. 8 Aircraft Layout Data8 pages
- Local Momentum Theory and Its Application To The Rotary WingNo ratings yetLocal Momentum Theory and Its Application To The Rotary Wing9 pages
- Fluid-Structure Interaction of Cropped Delta Wing With Experimental ValidationNo ratings yetFluid-Structure Interaction of Cropped Delta Wing With Experimental Validation14 pages
- Aerodynamic Coefficients of The Aircraft, Thrust Model and Geometric and Inertial PropertiesNo ratings yetAerodynamic Coefficients of The Aircraft, Thrust Model and Geometric and Inertial Properties6 pages
- Wing Design - Selection of Wing Parameters - 4 Topics: Airplane Design (Aerodynamic) Prof. E.G. Tulapurkara Chapter-5No ratings yetWing Design - Selection of Wing Parameters - 4 Topics: Airplane Design (Aerodynamic) Prof. E.G. Tulapurkara Chapter-59 pages
- Laboratory Report: Method: Real Time PCRNo ratings yetLaboratory Report: Method: Real Time PCR1 page
- Different Type of Glass and Its ApplicationNo ratings yetDifferent Type of Glass and Its Application2 pages
- Conservation and Management of Tropical Rainforests An Integrated Approach To Sustainability 2nd Edition BruenigNo ratings yetConservation and Management of Tropical Rainforests An Integrated Approach To Sustainability 2nd Edition Bruenig63 pages
- Adaptive Control Theory: Model Reference Adaptive SystemsNo ratings yetAdaptive Control Theory: Model Reference Adaptive Systems16 pages
- CIVIL LAW Answers To The BAR As Arranged by Topics (Year 1990-2006)0% (1)CIVIL LAW Answers To The BAR As Arranged by Topics (Year 1990-2006)5 pages
- Viva Vigan Binatbatan Festival of The Arts 2016 - Schedule of ActivitiesNo ratings yetViva Vigan Binatbatan Festival of The Arts 2016 - Schedule of Activities4 pages
- TDS Rate For The Fiscal Year 2025-2026 W.E f.1.7.2025 PDFNo ratings yetTDS Rate For The Fiscal Year 2025-2026 W.E f.1.7.2025 PDF29 pages
- Occupations Vocabulary Esl Crossword Puzzle Worksheets For KidsNo ratings yetOccupations Vocabulary Esl Crossword Puzzle Worksheets For Kids10 pages
- схема и сервис мануал на английском Sharp LC-39LE440U PDFNo ratings yetсхема и сервис мануал на английском Sharp LC-39LE440U PDF88 pages