Aerodynamics / Principle of Flight Q. 1/431 Exit
In what way is the longitudinal stability affected by the degree of
positive camber of the aerofoil?
Positive, because the centre of pressure shifts rearward at increasing
angle of attack.
Negative, because the lift vector rotates forward at increasing angle
of attack
Positive, because the lift vector rotates backward at increasing angle
of attack.
D > Noeffect, because camber of the aerofoil produces a constant pitch v
down moment coefficient, independent of angle of attack.
iat & \erodynamics / Principle of Flight Q. 2 /431
How would the exterior appearance of an aeroplane change, when
trimming for speed increase ?
A.) The elevator is deflected further up by a downward deflected trim
tab
The elevator is deflected further downward by means of a movable
horizontal stabiliser
( c The exterior appearance of the aeroplane will not change
Elevator deflection is increased further downward by an upward v
deflected trim tab
ey ait Hest & Aerodynamics / Principle of Flight Q. 3/431 Exit
Trailing edge flap extension will:
( A decrease the critical angle of attack and decrease the value of
CLmax.
B _ increase the critical angle of attack and decrease the value of CLmax.
( c ) decrease the critical angle of attack and increase the value of CLmax. 4p
D increase the critical angle of attack and increase the value of CLmax. 9
pp vaeae Next > serodynamics / Principle of Flight Q. 4 /431 Exit
The polar curve of an aerofoil is a graphic relation between :
(Al) 1S and stat speed
B_ Ansle of attack and cL x
CC ) Cand angle of attack
@® CLand cD v
ae eae Next > ‘erodynamics / Principle of Flight Q. 7 /431 Exit
The aft movement of the centre of pressure during the
acceleration through the transonic flight regime will:
A) decrease the static lateral stability.
B > increase the static longitudinal stability.
decrease the longitudinal stability.
D ) increase the static lateral stability.
ee Next & \erodynamics / Principle of Flight Q. 8 /431 Exit
The relative thickness of an aerofoil is expressed in:
A camber. x
B > meters.
( c degrees cross section tail angle.
D ® chord. Ze
tee ‘Rank &. \erodynamics / Principle of Flight Q. 12/431
The high lift device shown in the figure is a
A Slat
B Fowler flap
C Slotted flap
D Krueger flap
Prev Next >
Refer to information Aerodynamics / Principle of Flight Q. 13 /431 Exit
Which line represents the total drag line of an
aeroplane?
A lined
B Line « v
C tine a
oD Line b
+ Prev Next *
Refer to information
Drag a serodynamics / Principle of Flight Q. 14 /431 Exit
The max aft position of the centre of gravity is amongst others
limited by the:
A.) minimum value of the stick force per g. v
B_ maximum longitudinal stability of the aeroplane.
C_ maximum elevator deflection x
Do too small effect of the controls on the aeroplane.
ie Next » Aerodynamics / Principle of Flight Q. 15 /431 Exit
An A 310 aeroplane weighing 100 tons is turning at
FL 350 at constant altitude with a bank of 50
degrees. Its flight Mach range between low-speed
buffeting and highspeed buffeting goes from:
A.) N= 0.72 to M higher than 0.84
iB Me 0.65 to M higher than 0.84
CC M= 0.74 to M= 0.84 x
D "= 0.69 tom higher than 0.84 v
Exit terodynamics / Principle of Flight Q. 27 /431 Exit
Which point marks the value for minimum sink rate?
A Point a
B Point b
C Point x
D Point < o
« Prev Next >
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‘Aerodynamics / Principle of Flight Q. 30 /431 Exit
In transonic flight the ailerons will be less effective than in
subsonic flight because:
A. behind the shock wave pressure is lower.
B aileron down deflection moves the shock wave forward. x Aerodynamics / Principle of Flight Q. 31 /431 Exit
Which one of the following statements about the dynamic stability
of a conventional aeroplane about the lateral axis is correct?
A.) AnaftC.. position shortens the period time of the phugoid. x
B_) Damping of the phugoid is normally very weak. v
C Speed remains constant during one period of the phugoid.
D_ Period time of the phugoid is normally 5 sec.
4 Prey Next >» ‘Aerodynamics / Principle of Flight Q. 32 /431
The induced drag coefficient, CDi is proportional with:
A Clmax
qc
Exit Aerodynamics / Principle of Flight Q. 33 /431 Exit
Which of the following statements about the difference between
Krueger flaps and slats is correct?
A ) Deploying a Krueger flap will form a slot, deploying a slat does not.
Deploying a slat will increase critical angle of attack, deploying a
Krueger flap does not.
C_ Deploying a Krueger flap will increase critical angle of attack,
deploying a slat does not.
D Deploying a stat will form a slot, deploying a Krueger flap does not. v
; rex Next » Aerodynamics / Principle of Flight Q. 34/431
Differential aileron deflection:
A. is required to achieve the required roll-rate.
B__ cauals the drag of the right and left aileron.
is required to keep the total lift constant when ailerons are
alaliiaaheaal
Exit Aerodynamics / Principle of Flight Q. 36 /431
Which combination of speeds is applicable for structural strength
in gust (clean configuration) ?
A. 66 ft/sec and vb. x
(t/sec at all speeds.
65 ft/ ll speed
C55 ft/sec and vB.
Ne = Gust Inherit leaching
D Goitizedyind ve. Pr)
St To zocco ft.
« Prev. Next > ‘Aerodynamics / Principle of Flight Q. 37 /431 Exit
The centre of gravity moving aft wil
AQ ) increase the elevator up effectiveness. v
B decrease the elevator up effectiveness. x
C_ not affect the elevator up or down effectiveness.
D _ increase or decrease the elevator up effectiveness, depending on
wing location.
¢ Prev Next >» Aerodynamics / Principle of Flight Q, 38 /431 Exit
Compared with an oblique shock wave at the same Mach number a
normal shock wave has a
A) higher expansion.
B smaller compression.
C__ smatter expansion. \erodynamics / Principle of Flight Q. 39 /431 Exit
Which of the following statements about stall speed is correct ?
A. Decreasing the angle of sweep of the wing will decrease the stall v
speed.
B__ Increasing the angle of sweep of the wing will decrease the stall
speed.
c Use of a T-tail will decrease the stall speed.
D> Increasing the anhedral of the wing will decrease the stall speed.
¢ Prev Next > Aerodynamics / Principle of Flight Q, 40 /431 Exit
Examples of aerodynamic balancing of control surfaces are:
AL balance tab, horn balance, and mass balance. x
mass in the nose of the control surface, horn balance and mass
balance.
C spring tab, servo tab, and power assisted control.
servo tab, spring tab, seal between the wing trailing edge and the v
leading edge of control surface.
¢ Prev Next > Aerodynamics / Principle of Flight Q. 41/431 Exit
The value of the parasite drag in straight and level flight at
constant weight varies linearly with the:
A sauare of the speed. v
B speed.
C angle of attack Aerodynamics / Principle of Flight Q. 43 /431 Exit
What is the effect of a decreasing aeroplane weight on Mcrit at
, when flying at constant IAS ? The value of Mcrit:
A. _ is independent of the angle of attack. x
B decreases.
(C ) increases.
©& v Aerodynamics / Principle of Flight Q. 44 /431 Exit
The lift- and drag forces, acting on a wing cross section:
A. depend on the pressure distribution about the wing cross section. v
( B ) are normal to each other at just one angle of attack.
¢ c ) are proportional to each other, independent of angle of attack.
D_ vary linearly with the angle of attack. x Aerodynamics / Principle of Flight Q. 47 /431
The propeller blade angle of attack on a fixed pitch propeller is
increased when :
A velocity and RPM decrease
B__ RPM increases and forward velocity decreases v
C__ velocity and RPM increase
Exit Aerodynamics / Principle of Flight Q. 48 /431 Exit
When the trailing edge flaps are deflected in level flight, the
change in pitch moment will be:
A nose up.
B zero.
C dependent on c.g. location. Aerodynamics / Principle of Flight Q. 50 /431 Exit
Increasing the number of propeller blades will:
A. decrease the torque in the propeller shaft at maximum power.
B increase the maximum absorption of power. v
C _ increase the propeller efficiency. x ‘Aerodynamics / Principle of Flight Q. 52 /431 Exit
The critical angle of attack:
A decreases if the CG is moved aft x
B changes with an increase in gross weight
C_ remains unchanged regardless of gross weight v
D increases if the CG is moved forward
¢ Prev Next > ‘Aerodynamics / Principle of Flight Q. 53 /431 Exit
Constant-speed propellers provide a better performance than
fixed-pitch propellers because they:
A. produce a greater maximum thrust than a fixed-pitch propeller.
B__ have more blade surface area than a fixed-pitch propeller.
CC produce an almost maximum efficiency over a wider speed range. v \erodynamics / Principle of Flight Q. 54 /431 Exit
How are the speeds (shown in the figure) at point 1
and point 2 related to the relative wind/airflow V?
A Vi =Oand V2=V
B V1> V2andv2v v
D )¥1
Refer to information
Relative Wind VV,
= Stagnation Point -——
~“——— \erodynamics / Principle of Flight Q. 58 /431 Exit
Which aeroplane design has the highest probability of a super
stall?
A ATHail. v
B > Acanard wing.
C Swept wings. erodynamics / Principle of Flight Q. 59 /431
Why is a propeller blade twisted from root to tip?
A) To ensure that the root produces most thrust.
B_ > Toensure that the tip produces most thrust.
C_ Because the local angle of attack of a blade segment is dependent on
the ratio of that segment’'s speed in the plane of rotation and the true
airspeed of the aeroplane.
D__ Because the local angle of attack of a blade segment is dependent on
the ratio of that segment’s speed in the plane of rotation and the
angular velocity of the propellers.