LITERATURE SURVEY
To begin the design supersonic fighter aircraft, it is necessary to
study to access the need to feasibility of the proposed type of
supersonic fighter aircraft to evolve satisfactory specification to work
on. This literature survey is collection of various parameters of the
existing supersonic fighter like thrust to weight ratio, wing loading
aspect ratio span to length ratio overall dimension and the engine
specification are determined. It also helps for the study of
possibilities of introducing a new design concept, modifying
convectional design, and collection of data on the relevant power
plant. this literature survey also helps to get a decision on various
parameters and for the comparison of the parameters.
The survey of the various supersonic fighter aircraft and selection
of various parameters and their plots are as follows. The following
supersonic fighter aircraft are taken for survey.
MIG – 21
DASSAULT MIRAGR F1
ATLAS CHEETAH
HESA- SAEQEH
F-16 FIGHTING FALCON
AIDC F- CK -1
CHENGDU J-7
LITERATURE REVIEW
In the designers perspective it is necessary to compare the existing
airplanes that are of the same type as that of our desired airplane. Their
important parameters, positive aspects to be considered and pitfalls to be
overcome are taken into considerations. The data have been collected
from various sites from the internet for cargo aircraft design. Several
parameters are compared for over 30 aircrafts and different critical
parameters were plotted on graph. They are
Cruise velocity
Range
Wing area
Thrust/weight ratio
Empty weight
Maximum take-off weight
Length
Wingspan
Aspect ratio
Thrust
Power plant
Service ceiling
COMPRATIVE DATA SHEET
SPECIFICATION Length Wing Height Wing Empty Loaded Max. takeoff Cruise
(m) span (m) Area Weight Weight weight Speed
(m) (m2) (kg) (kg) (kg) (km/h)
AIDC F-CK-1 14.48 9 4.5 24.2 6500 9072 20000 1980
Atlas cheetah 15.5 8.22 4.5 35 6600 9500 13700 2090
Mirage f1 15.3 8.4 4.5 25 7400 10900 16200 056
Mirage IIIV-01 18 8.72 5.55 26 8300 12000 18700 2350
EWR VJ 101 15.7 6.67 4.1 23.2 3500 5700 6100 1075
F-16 Fighting 15.06 9.96 4.88 27.87 8570 12000 19200 1850
falcon
F11F-1/F-11A 14.3 9.6 4 23 6277 9561 10663 920
F11F-1F 14.85 9.65 4.36 23.25 6277 9561 11833 1950
HESA Saeqeh 15.89 8.13 4.2 24 4400 9000 19000 1520
Chengdu –J7 14.885 8.32 4.11 24.88 5292 7540 9100 1975
IAI-Nammer 16 8.22 4.55 34.8 12500 16511 22000 2205
MC-Donnel 20.55 12.09 5.49 34.2 12925 20715 23700 1600
F-101B
MIG-29 17.37 11.4 4.73 38 11000 15300 20000 2250
MIG-35 17.3 12 4.7 38 11000 17500 29700 2200
MIG-19 12.5 9 3.9 25 5447 7500 7560 1200
SPECIFICATION Range Service Rate of Max. Aspect Wing Thrust/weight
(Km) ceiling(m) climb speed(k ratio loading Ratio
(m/min) m/h) (kg/m2)
AIDC F-CK-1 1100 16800 14000 2205 3.34 360 1.01
Atlas cheetah 1300 17000 14000 2350 1.93 250 0.98
Mirage f1 1500 20000 14580 2.82 420 0.78
Mirage IIIV-01 1250 23000 12500 2632 2.92 440 1.05
EWR VJ 101 900 12000 15500 1274 1.88 22 0.20
F-16 Fighting 4220 15240 15240 2120 3.55 431 1.095
falcon
F11F-1/F-11A 2050 14960 4980 1170 4 411 0.75
F11F-1F 1826 19980 9500 2253 4 415 0.65
HESA Saeqeh 3000 16000 10500 1700 2.75 375 1.03
Chengdu –J7 2200 17500 11700 2200 2.8 300 0.95
IAI-Nammer 1382 17700 16700 2495 1.94 470 0.85
MC-Donnel 2450 17800 15000 1825 4.27 607 0.74
F-101B
MIG-29 1430 18013 19800 2400 3.42 400 1.09
MIG-35 2000 17500 19800 2400 3 330 1.03
MIG-19 1390 17500 19800 1455 3.24 200 0.86
GRAPH OF VARIABLES PARAMETERS
Cruise speed vs Length
25
AIDC F-CK-1
20 CHEETAH
Mirage f1
mirage III-01
Length (m)
15
EVR VJ 101
10 F-16 FIGHTING FALCON
FIIF-1
5 F11F-1F
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Wing span
14
AIDC F-CK-1
12
CHEETAH
10 Mirage f1
Wing span (m)
mirage III-01
8
EVR VJ 101
6
F-16 FIGHTING FALCON
4 FIIF-1
F11F-1F
2
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
6
Cruise speed vs Height
AIDC F-CK-1
5
CHEETAH
4 Mirage f1
mirage III-01
Height (m)
3 EVR VJ 101
F-16 FIGHTING FALCON
2 FIIF-1
F11F-1F
1 HESA
CHENGDU-J7
0
IAI NAMMER
0 500 1000 1500 2000 2500
Cruise speed (m/s)
Cruise speed vs Wing area
40
AIDC F-CK-1
35
CHEETAH
30
Mirage f1
Wing area(m^2)
25 mirage III-01
20 EVR VJ 101
15 F-16 FIGHTING FALCON
FIIF-1
10
F11F-1F
5
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Empty weight
14000
AIDC F-CK-1
12000
CHEETAH
10000 Mirage f1
Empty weight (kg)
mirage III-01
8000
EVR VJ 101
6000
F-16 FIGHTING FALCON
4000 FIIF-1
F11F-1F
2000
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Loaded weight
25000
AIDC F-CK-1
20000 CHEETAH
Mirage f1
Loaded weight(kg)
15000 mirage III-01
EVR VJ 101
10000 F-16 FIGHTING FALCON
FIIF-1
5000 F11F-1F
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Max. takeoff weight
35000
AIDC F-CK-1
30000
CHEETAH
Max. takeoff weight(kg)
25000 Mirage f1
mirage III-01
20000
EVR VJ 101
15000
F-16 FIGHTING FALCON
10000 FIIF-1
F11F-1F
5000
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Range
4500
4000 AIDC F-CK-1
3500 CHEETAH
Mirage f1
3000
mirage III-01
Range (km)
2500
EVR VJ 101
2000 F-16 FIGHTING FALCON
1500 FIIF-1
F11F-1F
1000
HESA
500
CHENGDU-J7
0 IAI NAMMER
0 500 1000 1500 2000 2500
Cruise speed (m/s)
Cruise speed vs Service ceiling
25000
AIDC F-CK-1
20000 CHEETAH
Mirage f1
Service ceiling (m)
15000 mirage III-01
EVR VJ 101
10000 F-16 FIGHTING FALCON
FIIF-1
5000 F11F-1F
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Max. speed
3000
AIDC F-CK-1
2500 CHEETAH
Mirage f1
Max. speed (km/h)
2000
mirage III-01
1500 EVR VJ 101
F-16 FIGHTING FALCON
1000
FIIF-1
500 F11F-1F
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Rate of climb
25000
AIDC F-CK-1
20000 CHEETAH
Rate of climb (m/min)
Mirage f1
15000 mirage III-01
EVR VJ 101
10000 F-16 FIGHTING FALCON
FIIF-1
5000 F11F-1F
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Aspect ratio
4.5
4 AIDC F-CK-1
CHEETAH
3.5
Mirage f1
3
Aspect ratio
mirage III-01
2.5
EVR VJ 101
2
F-16 FIGHTING FALCON
1.5
FIIF-1
1
F11F-1F
0.5 HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Wing loading
700
AIDC F-CK-1
600
CHEETAH
Wing loading (kg/m^2)
500 Mirage f1
Mirage IIIv-01
400
EVR VJ 101
300
F-16 FIGHTING FALCON
200 FIIF-1
F11F-1F
100
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
Cruise speed vs Thrust /weight ratio
1.4
AIDC F-CK-1
1.2
CHEETAH
1 Mirage f1
Thrust/weight ratio
mirage III-01
0.8
EVR VJ 101
0.6
F-16 FIGHTING FALCON
0.4 FIIF-1
F11F-1F
0.2
HESA
0 CHENGDU-J7
0 500 1000 1500 2000 2500
IAI NAMMER
Cruise speed (m/s)
DESIGN DATA SHEET
Specification :
Length : 15 m
Wing span : 9m
Height : 4.5 m
Wing area : 25 m2
Empty weight : 6500 kg
Loaded weight : 9500 kg
Max. takeoff weight : 20000 kg
Range : 2100 km
Service ceiling : 17000 m
Max. speed : 2200 km/h
Rate of climb : 14000 m/min
Aspect ratio : 2.8
Wing loading : 300 kg/m2
Thrust/weight ratio :1
SFC :2.5×10-4 per second
Payload + crew : 10500 kg
Endurance : 6.944×105 m
WEIGHT ESTIMATION
WEIGHT ESTIMATION
The weight of the aircraft under design is to be estimated this done by
finding the individual weight ratio’s from the mission profile.
MISSION PROFILE FOR MILITARY FIGHTER AIRCRAFT :
1. Warm-up weight & Takeoff weight:
The value for this stage is given fixed standard
W1/W0=0.970
Where, W0 = Initial weight of aircraft
W1 = weight at takeoff
2. Climb
The value for this stage is given fixed standard
W2/W1=0.970
Where, W2 = weight at beginning of cruise
3. Cruise
The value for this stage is given by formula,
W3/W2= e-[RC/V(L/D)max.]
Where, R = Range
W3 = Weighted at the end of cruise
V = Max. velocity
L/D = Lift to drag ratio
From the graphs,
Swet/Sref =4
Wetted aspect ratio(b2/Swet) = 0.81
(L/D)max = 12.5
Specific fuel consumption C =2.5×10-4 kg per second
Already we know,
R = 21×105 m ;
C =2.5×10-4 kg per second
V = 611.12 m/s
(L/D)max. For cruise = 0.866 (L/D)max.
W3/W2 = e-[(2100000×0.00025)/(611.12×0.866×12.5)]
= 0.923
Cruise 1, W3/W2 = 0.923
4. Descent :
The weight ratio for this phase is given by,
W4/W3 = 0.995
5. Cruise 2 = e-[RC/V(L/D)max.]
R = 21×105 m ;
C =2.5×10-4 kg per second
V = 611.12 m/s
(L/D)max. for cruise = 0.866 (L/D)max.
W5/W4 = e-[(2100000×0.00025)/(611.12×0.866×12.5)]
W5/W4 = 0.923
6. Loiter :
W6/W5 = e-[EC/V(L/D)max.]
E = 6.944×105
C =2.5×10-4 kg per second
=e-[(694400×0.00025)/(611.12×12.5)]
Loiter, W6/W5 = 0.977
7. Landing :
The weight ratio for this phase is fixed value is given by
W7/W6 = 0.995
WEIGHT CALCULATIONS :
The total weight ratio is given by
W7/W0 = W7/W6 ×W6/W5× W5/W4× W4/W3 ×W3/W2 ×W2/W1 ×W1/W0
=0.995× 0.977× 0.9237× 0.995× 0.9237× 0.985× 0.970
= 0.7885
Fuel weight fraction :
The fuel fraction ratio is given by
Wf/W0 = 1.06[1-( W7/W0)]
Wf/W0 =1.06(1-0.7885) = 0.224
Empty weight fraction :
To determine the empty weight of the aircraft, we use following
relationship.
We/W0 = 0.93(W0)-0.07
(W0)actual = (Wcrew +Wpayload)/(1-We/W0-Wf/W0)
We solve the above equation by iteration and the values are tabulated as
follows
S. No (W0)guess We/W0 (W0)actual
1. 50000 0.4360 30882.35
2. 50100 0.4360 30882.35
3. 50200 0.4357 30885.13
4. 50300 0.4358 30864.19
5. 50400 0.4358 30864.19
6. 50500 0.4358 30864.19
7. 50510 0.4357 30885.13
8. 50520 0.4357 30885.13
9. 50530 0.4357 30885.13
10. 50535 0.4357 30885.13
11. 50540 0.4357 30885.13
(W0) actual = 30885.13 kg
We/W0 = 0.93(W0)-0.07
=0.93(30885.13)-0.07
= 0.4510
We/W0 = 0.4510.
