1.

GENERAL DESCRIPTION OF AIRPLANE

Name of the airplane Sukhoi su-30 Airbus Cessna 150 Antonov
A330-300 AN-140
Type of airplane Fighter jet Passenger Private Jet Passenger/cargo
Country of origin Russia France USA Ukraine
2.TYPE OF POWER PLANT
Name AL-31FP Rolls-Royce Continental O- Pratt & Whitney
Trent 700 200 Canada PW127A
Engine rating 12,500 kgf 72000 lbf 100 HP 2051 (SHP)
Weight of power plant 1570 kg 6200 kg 170 kg 546 kg
Overall dimensions of 1.09 2.47 0.63 0.78
engine
Diameter (m)
Length (m) 4.96 4.27 0.6 1.56
No. of engines and 2 engines located 2 engines 1 engine 2 engines
their locations in nacelles on located on located in nose located on the
either side of the wings of the aircraft wings
fuselage
3.WING
Span (m) 14.7 60.3 10.16 24.73
Tip chord (m) 1.6 1.6 0.4 1.6
Mean chord (m) 4.2 4.1 1.46 4.2
Sweep (∧𝑂 ) 42o 42o 0o 0o
Twist (O) -2o -2o -2o -2o
Flap area (m2) 3.5 22 1.19 14.4
Type of high-lift Leading edge Trailing edge Trailing edge Trailing edge
devices slats & trailing flaps flaps flaps
edge flaps
Location of spars Two spars located Two spars One spar Two spars
at 25% & 65% of located at located at 50% located at 25%
chord 25% & 65% of of chord & 65% of chord
chord
Taper ratio () 0.24 0.251 0.24 0.36
Root chord (m) 6.6 6.6 1.68 6.6
Area (S) (m2) 62 363.100 15 51
Mean aerodynamic 3.8 7.260 1.37 3.8
chord (m)
Dihedral. ( 0) 1.5o 5o 3o 6o
Incidence (i0w) 2o 2o 1o 2o
Aileron area (m2) 7.2 32 3.1 7.2
Flap area/wing area or 0.2322 0.1 0.08 0.282
Sflap/S
Flap chord/ wing chord 0.182 0.1 0.2 0.18
or cflap/cwing
Aileron chord/wing 0.136 0.062 0.38 0.13
chord or caileron/cwing
Location of wing on Mid wing Low wing High wing High wing
fuselage (high
wing/mid wing/low
wing)
Aspect ratio (A) 3.5 9.265 6.9 11.7
Aileron area/wing area 0.1161 0.088 0.21 0.147
or Saileron/S
4. HORIZONTAL TAIL SURFACE
Platform shape Trapezoidal Trapezoidal Rectangular Rectangular
Span (m) 6.38 19.7 7.32 16.2
Tip chord (m) 1.25 2.1 1.22 2.50
Area (m2) 14.8 64 8.92 18
Incidence (i0 t) 0 o
0o 0o 0o
Elevator area (m2) 3.6 12.8 1.2 4
Aspect ratio 2.75 6.05 5.9 6.80
Elevator area / Tail 0.243 0.4 0.13 0.22
area
Tail area (Sht) / wing 0.238 0.176 1.12 0.2
area(S)
Elevator chord / tail 0.204 0.126 0.1 0.11
chord
Construction and other The horizontal tail Horizontal tail The horizontal The horizontal
details sections are sections are tail sections are tail sections are
made of titanium made of high made of high made of high
and high strength strength of Al- strength of Al- strength of Al-
of Al-Alloys Alloys Alloys Alloys
Root chord (m) 2.94 6.3 1.52 2.7
Sweep 42o 35o 0o 30o
Tab area (m2) 0.36 1.28 - 0.4
Taper ratio 0.43 0.360 - 0.438
Tab area / elevator 0.1 0.1 - 0.1
area
5. VERTICAL TAIL SURFACE
Airfoil NACA 0012 NACA 0012 NACA 0012 NACA 0012
Height (m) 5.93 16.9 1.98 8.225

Tip chord (m) 1.05 1.73 0.61 1.2

Area (m2) 9.6 13 2.69 5.1
Rudder area (m2) 1.7 5.5 0.56 2.8
Aspect ratio (Av) 2.8 1.8 3.8 2.7
Rudder area/tail area 0.18 0.078 0.21 0.5
Tab area / rudder area 0.3 0.15 0.1
Tail area (Svt)/wing 0.34 0.22 0.1
area(S)
Type of control and Conventional Conventional Conventional Conventional
aerodynamic balancing control surfaces control control surfaces control surfaces
with aerodynamic surfaces with
balance aerodynamic
balance
Root chord (m) 2.5 4.8 1.22 1.42
Sweep 42o 42o 30o 25o
Tab area (m2) 0.36 0.42 - 0.42
Taper ratio 0.3 0.350 0.4 0.5
6. FUSELAGE
Length (m) 21.935 64 6.69 22.60
Length of nose (lnose) 4.9 - - -
Length of cockpit 3.5 16.53 1.27 -
(lcockpit)
Volume of cabin(m3) 9.4 215 - 65.5
Cockpit 2 2 2 2
Number of seats
Cockpit instruments Head-up Airspeed Airspeed Airspeed
instrument(HUD), indicator, indicator, indicator,
Multifunction altimeter, vertical speed vertical speed
displays (MFDs) vertical speed indicator, indicator,
indicator altimeter altimeter
Vision (angle) The pilot has a The pilot has The pilot has a The pilot has a
30o field of view a field view of field view of field view of
to right & left and approximately approximately approximately
20o field of view 180o 180o 180o
up & down
Construction and other The su-30 Airframe is The airframe is The airframe is
details airframe is made made of Ti & made of Al-alloy made of Ti and
of Ti and high high intensity and the twin high intensity of
intensity of Al- of Al-alloy.The stabilizers and Al-alloys. The
alloys.The twin twin stabilizer horizontal tail twin stabilizers
stabilizers and & horizontal consoles are and horizontal
horizontal tail tail consoles joined to tail tail consoles are
consoles are are joined to beam. joined to tail
joined to tail tail beam. beam.
beam.
Length(lf)/wingspan(b) 1.49 0.26 0.81 0.92
lnose/lf 0.22 - - -
lcockpit/lf 0.16 0.25 0.19 -
7. LANDING GEAR
Type of landing gear Hydraulically Hydraulically Tricycle-type Hydraulically
retractable retractable retractable
tricycle-type tricycle-type tricycle-type

Number of wheels Main:1 Main:4, Main:2, Main:2,

Nose:2 Nose:2 Nose:1 Nose:1
Tyre pressure(kgf/cm2) 15.5 15.7 1.687 10.5
Wheel base (m) 7.76 25.38 1.98 4.5
Wheel tread (m) 4.92 10.68 1.52 3.6
Location of landing 2 main landing Main: in thee 2 main Landing The location of
gears gear located wing-root, gear Under the the landing
under wings and Nose: in the wings & one at gears is on the
1 at nose of the forward nose of the fuselage& nose
aircraft fuselage aircraft of the aircraft

Means to reduce Drag chute and Spoilers and Flaps and Flaps
landing run thrust vectoring thrust brakes
nozzles reversers
8. OVERALL DIMENSIONS OF AIRPLANE
Length (m) 21.935 63.69 7.29 22.61
Height (m) 6.36 16.83 2.59 8.23
Landing gear wheel 7.76 25.38 1.95 7.76
base(m)
Wing span (m) 14.7 60.30 10 24.51
Landing gear wheel 4.92 10.68 1.1 4.92
tread (m)
Length/span 1.49 1.06 0.72 0.92
Tread/span 0.33 0.18 0.11 0.20
Height/span 0.43 0.28 0.26 0.34
9. WEIGHTS
Pay load (kgf) 8000 45900 300 6000
Empty weight (kgf) 17700 120100 481 12810
Fuel weight (kgf) 9400 97530 118 4500
Structural weight (kgf) 18400 121700 499 21500
Disposable load (kgf) 16100 143430 726 10000
Landing weight (kgf) 25500 182000 726 21500
Normal gross weight 24900 217700 726 21500
(kgf)
Maximum gross 34500 242000 726 21500
weight (kgf)
Payload/gross weight 0.32 0.19 0.34 0.28
Empty weight/gross 0.71 0.50 0.66 0.60
weight
Fuel weight/gross 0.38 0.40 0.16 0.21
weight
Structural 0.74 0.50 0.69 1.00
weight/gross weight
Wing loading (kgf/m2) 401 662 45 390
Power (or thrust) 0.86 2.67 4.81 3.58
loading (kgf/kW)
10. PERFORMANCE
Maximum speed 1350 855 185 540
(kmph) at sea level
Maximum speed 2120 880 188 575
(kmph) at altitude
Landing speed (kmph) 260 260 80 200
Cruise speed (kmph) 1800 at 11 871 at 10.67 160 at 10 460 at 7.6
and altitude (km)
Maximum sea level 18000 1200 213 560
rate of climb (m/min)
Service ceiling (km) 17.3 12.5 4.3 7.6
Range or radius of 3000 11750 550 2100
action (km)
Endurance (hours) 3.75 14 3.5 6
Take-off run (m) 550 2780 300 1100
Landing run (m) 750 1400 250 1000
 1. GENERAL DESCRIPTION OF AIRPLANE
Name of the airplane Boeing 747 Lockheed Bombardier Boeing 737
Martin F-35 Learjet 75
Lightning II Liberty
Type of airplane Commercial Fighter jet private jets Cargo
Name of manufacturer Boing & Lockheed Bombardier Boing & America
and America Martin & & Canada
country of origin American

2. TYPE OF POWER PLANT

Name Pratt & Pratt & Garrett Pratt & Whitney
Whitney Whitney TFE731 JT8D
JT9D F135
turbofan
engines
Engine rating 46,300 to 28,000 lbf 3,500 to 12,250 to 17,400
50,000 lbf (125 kN) and 5,000 pounds pounds-force (54
(205.95 to 43,000 lbf (15.57 to to 77 kN)1.
222.41 kN) (191 kN) 22.24 kN)2.
take-off2 with
afterburner
Specific fuel consumption 0.6 lb/lbf/hr 0.70 lb/lbt/hr 0.469-0.517 0.744 kg/daN/h
(61.16 (dry), 2.0 lb/lbf/hr (0.730 lb/lbf/h)1.
kg/kN/hr) at lb/lbt/hr (with (0.0133-
M0.8 at afterburner) 0.0146
35,000 ft kg/kN/s)3.
(11,000 m)
Oil consumption ----- ----- --------- ---------
Weight of power plant 8,470 lb 3,750 lb 1,700 kg 3,400 to 4,000
(3,840 kg) (1,700 kg)3 (3,750 lb)3 pounds (1,500 to
1,800 kg)2.
Overall dimensions of
engine 2.37 meters3 1.1 meters4 1 meter2 1.37 meters2.
Diameter (m)
Length (m) 3.37 meters3 5.6 meters4 1.5 meters3 4.28 meters2.

Engine center of gravity -------- ------- --------- ----------

Special accessories and -------- ------- ------- ----------
controls
No. of engines and their Four and two One and Two and Two and mounted
locations mounted on center axis mounted on on each wing
each wing the rear
fuselage
3. WING
Airfoil section NACA 64A- NACA 64A- NACA NACA 65-410
514 204 23015.5
Span (m) 68.45 10.7 14.76 35.79
Tip chord (m) 4.11 1.22 1.09 1.68
Mean chord (m) 8.32 3.05 2.74 4.17
Sweep (∧𝑂 ) 37.5° 35° 13° 25°
Twist (O) -2° 0° -2° -2°
Flap area (m2) 153.3 8.54 4.27 37.38
Type of high-lift devices Triple slotted Leading-edge Single-slotted Single-slotted flaps
trailing edge flaps and flaps and Krueger flaps
flaps and trailing-edge
Krueger style flaps
leading edge
slats
Location of spars 25% and 65% 25% and 65% 25% and 65% 25% and 65% of
of chord of chord of chord chord
Taper ratio () 0.3 0.4 0.4 0.2
Root chord (m) 14.84 5.49 6.01
4.57

Area (S) (m2) 511 42.7 21.37 124.6

Mean aerodynamic chord 8.32 3.05 2.74 4.17
(m)
Dihedral. ( 0) 6° 0° 3° 6°
Incidence (i0w) 1° 0° 1° 1°
Aileron area (m2) 26.8 2.1 1.07 7.8
Flap area/wing area: or 0.3 0.2 0.2 0.3
Sflap/S
Flap chord/ wing chord or 0.25 0.2 0.2 0.25
cflap/cwing
Aileron chord/wing chord 0.15 0.1 0.1 0.15
or caileron/cwing
Location of wing on Low wing Mid wing Low wing Low wing
fuselage (high wing/mid
wing/low wing)
Construction and other Aluminium Composite Aluminium alloy
details alloy structure structure with Aluminium structure with
with stealth coating alloy structure composite fairings
composite with
fairings composite
fairings

Aspect ratio (A) 7.91 3.5 5.92 9.45

Aileron area/wing area or 0.052 0.049 0.05 0.063
Saileron/S
4. HORIZONTAL TAIL SURFACE
Type of horizontal tail Conventional All-moving Conventional Conventional
Platform shape Trapezoidal Trapezoidal Trapezoidal Trapezoidal
Span (m) 22.17 6.65 5.03 12.04
Tip chord (m) 2.13 1.07 0.61 1.22
Area (m2) 78.62 9.29 7.43 27.87
Incidence (i0 t) -1° Variable -1° -1.5°
Elevator area (m2) 26.01 N/A 2.47 9.29
Aspect ratio 6.3 3.7 3.4 5.2
Elevator area / Tail area 0.33 N/A 0.33 0.33
Tail area (Sht) / wing 0.15 0.11 0.28 0.25
area(S)
Elevator chord / tail chord 0.33 N/A 0.33 0.33
Location of Horizontal tail Below the Above the Below the Below the vertical
vertical tail vertical tail vertical tail tail
Type of control and Conventional Stabilator Conventional Conventional
aerodynamic balancing elevator with with elevator with elevator with trim
trim tabs differential trim tabs tabs
deflection
Construction and other Aluminium Composite Aluminium Aluminium alloy
details alloy and structure with alloy and structure with
structure with stealth structure with composite fairings
composite coating composite
fairings fairings
Airfoil NACA 0012 NACA 64A- NACA 0012 NACA 0012
204
Root chord (m) 4.72 1.86 1.98 3.05
Sweep 37° 35° 35° 28°
Tab area (m2) 0.82 N/A 0.12 0.46
Taper ratio 0.45 0.58 0.31 0.4
Tab area / elevator area 0.03 N/A 0.05 0.05
5. VERTICAL TAIL SURFACE
Type of vertical tail Conventional Conventional Conventional Conventional
Airfoil NACA 0012 NACA 64A- NACA 0012 NACA 0012
204
Height (m) 9.4 4.01 2.44 5.79
Tip chord (m) 2.13 0.76 0.61 1.22
Area (m2) 55.2 7.43 4.65 32.4
Off-set angle 0° 0° 0° 0°
Rudder area (m2) 18.4 2.47 1.54 10.8
Aspect ratio (Av) 1.6 1.3 3.3
2.2

Rudder area/tail area 0.33 0.33 0.33 0.33

Tab area / rudder area 0.04 0.08 0.04
N/A

Tail area (Svt)/wing 0.1 0.07 0.17 0.2

area(S)
Rudder chord/V.tail chord 0.33 0.33 0.33 0.33
Type of control and Conventional Conventional Conventional Conventional
aerodynamic balancing rudder with rudder with rudder with rudder with trim
trim tabs trim tabs trim tabs tabs
Construction and other Aluminium Composite Aluminium Aluminium alloy
details alloy structure structure with alloy structure structure with
with stealth coating with composite
composite composite fairingsAluminium
fairings fairings alloy structure with
composite fairings
Root chord (m) 4.72 1.86 1.98 3.05
Sweep 37° 35° 28°
35°

Tab area (m2) 0.74 0.12 0.43

N/A

Taper ratio 0.45 0.41 0.31 0.4

Location Below the Above the Below the Below the
horizontal tail horizontal tail horizontal tail horizontal tail
6. FUSELAGE
Length (m) 70.6 15.7 17.7 35.6
Length of nose (lnose) 8.5 3.5 3.5 6.5
Length of cockpit (lcockpit) 8.5 N/A 3.7 8
Length of tail cone 9.5 4.5 4.4 10
(ltailcone)
Length of payload 37.1 N/A 6.1 11.1
compartment
Length of mid-fuselage 7 7.2 0 0
Upsweep angle 10° 15° 8° 12°
Fuselage closure angle 30° 35° 20° 25°
Shape and size of cabin Double-deck, Single-seat, Cylindrical, Cylindrical, 3.54 m
6.1 m 1.52 m width, 1.56 m diameter, 28.47 m
diameter, 2.36 m length diameter, 5.39 length
57.55 m length m length
Arrangement of payload Underfloor Internal Underfloor Underfloor cargo
and auxiliary equipment cargo weapons bay, cargo compartments,
compartments, external compartment, overhead bins,
overhead bins, hardpoints, overhead galleys, lavatories
galleys, fuel tanks, bins, galleys,
lavatories, avionics lavatories
upper deck
lounge
Cockpit: 2 1 2 2
Number of seats

Cockpit instruments Glass cockpit with

Glass cockpit Glass cockpit Glass cockpit six LCD screens,
with six LCD with large with four head-up display,
screens, head- touch-screen LCD screens, fly-by-wire controls
up display, fly- display, Garmin
by-wire helmet- G5000
controls mounted avionics, fly-
display, by-wire
voice- controls
activated
controls

Vision (angle) 200° 360° 200° 200°

Construction and other Aluminium

details Aluminium Composite alloy structure Aluminium alloy
alloy structure structure with with structure with
with stealth coating composite composite fairings
composite fairings
fairings

Length(lf)/wingspan(b) 0.69 2.04 1.14 1.06

lnose/lf 0.1 0.2 0.15 0.15
lcockpit/lf 0.1 0.1 0.1 0.1
ltailcone/lf 0.1 0.2 0.15 0.15
 7. LANDING GEAR
Type of landing gear tricycle-type, tricycle-type, tricycle-type, tricycle-type,
retractable retractable retractable retractable
Number and size of two nose two nose two nose two nose wheels
wheels wheels wheels wheels (27x7.75 inches),
(40x16 (20x7.5 (18x5.5 eight main wheels
inches), 16 inches), four inches), four (37x12 inches)
main wheels main wheels main wheels
(49x19 (25x8.5 (22x6.75
inches) inches) inches)
Tyre pressure 200-220 psi 300 psi for 185 psi for 170-210 psi for
for nose nose wheels, nose wheels, nose wheels, 170-
wheels, 195- 325 psi for 160 psi for 225 psi for main
225 psi for main wheels main wheels wheels
main wheels
Wheel base (m) 25.6 m 5.3 m 7.0 m 11.1 m
Wheel tread (m) 18.3 m 2.6 m 4.3 m 9.1 m
Location of landing gears nose gear nose gear nose gear nose gear under
under the under the under the the cockpit, main
cockpit, main cockpit, main cockpit, main gears under the
gears under gears under gears under wings
the wings and the wings the fuselage
the fuselage
Means to reduce landing thrust drag chute, thrust thrust reversers,
run and other details reversers, thrust reversers, spoilers,
spoilers, vectoring (for spoilers, anti- autobrakes
autobrakes F-35B) skid brakes
8. OVERALL DIMENSIONS OF AIRPLANE
Length (m) 70.7 15.7 17.7 39.5
Height (m) 19.4 4.4 4.3 12.5
Landing gear wheel 25.6 5.3 7.0 11.1
base(m)
Wing span (m) 68.4 10.7 15.5 35.8
Landing gear wheel tread 18.3 2.6 4.3 9.1
(m)
Length/span 1.03 1.47 1.14 1.10
Tread/span 0.27 0.24 0.28 0.25
Height/span 0.28 0.41 0.28 0.35
9. WEIGHTS
Pay load (kgf) 134,000 8,160 kgf 9,545 kgf 20,412 kgf
Empty weight (kgf) 485,300 kgf 13,290 kgf 6,300 kgf 41,413 kgf
Fuel weight (kgf) 170,600 kgf 8,278 kgf 2,750 kgf 20,882 kgf
Structural weight (kgf) 272,900 kgf ---------- ------------- ----------
Disposable load (kgf) 526,100 kgf 8,160 kgf 9,545 kgf 20,412 kgf
Landing weight (kgf) 312,100 kgf ---------- 8,709 kgf 65,823 kgf
Normal gross weight (kgf) 422,300 kgf 22,680 kgf 9,752 kgf 62,823 kgf
Maximum gross weight 447,700 kgf 31,800 kgf 9,752 kgf 79,016 kgf
(kgf)
Payload/gross weight 29.9% 0.26 0.98 0.26
Empty weight/gross 108.5% 0.42 0.65 0.52
weight
Fuel weight/gross weight 36.0% 0.26 0.28 0.26
Structural weight/gross 61.3% ---------- --------------- ------------
weight
Wing loading 1,120 kgf/m 430 kgf/m 433 kgf/m 666 kgf/m
Power (or thrust) loading 3.9 kgf/kw 0.72 0.40 0.36
10. PERFORMANCE
Maximum speed (kmph) 912 km/h 1,930 km/h 1,930 km/h 912 km/h
at sea level
Maximum speed (kmph) 945 km/h 1,930 km/h 1,930 km/h 945 km/h
at altitude
Landing speed (kmph) 260 km/h 278 km/h 278 km/h 260 km/h
Cruise speed (kmph) and 840 km/h and 1,200 km/h 1,200 km/h 840 km/h and 10.7
altitude (km) 10.7 km and 12 km and 12 km km3
Maximum sea level rate 1,524 m/min 3,050 m/min 3,050 m/min 1,524m/min
of climb (m/min)
Service ceiling (km) 12.5 kM 15.2 km 15.2 km 12.5 km
Range or radius of action 5.66 km 2,220 km 2,220 km 5,665km
(km)
Endurance (hours) 6.5 hours 2.36 hours 2.36 hours 6.5 hours
Take-off run (m) 2,134 m 457 m3 457 m 2,134 m
Landing run (m) 1,701 m 513 m3 518 m 1,701 m