Aircraft Design Project – I Presentation

8/12/2019 Aircraft Design Project I Presentation

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Submitted byMUKESH K

(720811101025)NAGARAJAN G

(720811101026)NARAYANAMOORTHY M

(720811101027)NAVEENKUMAR T

(720811101029)

THIRD YEAR, B.EAERONAUTICAL ENGINEERING

HINDUSTHAN INSTITUTE OF

TECHNOLOGY

COIMBATORE - 641 032ANNA UNIVERSITY CHENNAI -


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Classification of AircraftsDesign ProcessDesign Proposal of HP-42 MRTTAerial RefuelingComparative Study and Preliminary Design

DataPreliminary Weight EstimationAirfoil Selection and Main Wing DesignFuselage DesignLanding Gear DesignTail DesignEngine Selection3-View Diagram


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Students view

of design

The realdesign process


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Aerial refueling, also referred to as air

refueling, in-flight refueling(IFR), air-to-

air refueling(AAR), and tanking, is the

process of transferring fuel from oneaircraft (the tanker) to another (the

receiver) during flight.


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Aspect Ratio

Wing Span

Wing Area

Thickness to

chord Ratio

Sweep BackAngle

Height

Fuselage

Length

Empty Mass

Maximum

Take-off Mass

Maximum

Landing Mass

Thrust to

Weight Ratio Wing Loading

Number of

Engines

Thrust per

Engine

Fuel

Economy Maximum

Speed

Cruise

Speed

Absolute

Ceiling

Service

Ceiling

Range

Ferry

Range Endurance


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General characteristics: Crew:6 (2 pilots, 3rd optional, 3

loadmasters)

Capacity (Max. Payload):

1,58,620 kg

Aspect Ratio: 7.75

Fuselage Length:58.33 m Height:16.25 m

Wingspan:65 m

Wing Area:550 sq. m

Thickness-to-Chord Ratio:

13.79 % of chord

Sweep Back Angle: 24.25 (at

25% of chord)

Empty Mass:1,66,538 kg

Maximum Takeoff Mass:

3,64,706 kg

Maximum Landing Mass:

2,86,363 kg

Powerplant:4 232.6 kN each

Fuel Economy:0.0615 km/ltr

Performance:Maximum Speed: 892.3 km/hr,

Mach 0.835

Cruising speed:768.75 km/hr,

Mach 0.72

Absolute Ceiling: 11,500 m

Service Ceiling:10,000 m

Range:9,273 km (maximum long

range cruise speed), 4,885.15 km

(with full load)

Ferry range:11,125 km

Endurance: 14.375 hrs

Loiter time:35 minutes

Tactical takeoff distance:3,562.5m (ISA, MSL)


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ENGINE START-UP

AND TAKE-OFF

CLIMB AND

ACCELERATE TO

CRUISE

CONDITIONS

CRUISE OUT TO

DESTINATION

LOITER LANDING

Representative flight plan for

the Tanker aircraft

Mass Initial Values

(Before Iteration)

Final Values (After

Iteration)

Maximum Take-Off

Mass

3,64,706 kg 5,44,475.4801 kg

Maximum Landing

Mass

2,86,363 kg 2,22,200.0969 kg

Empty Mass 1,66,538 kg 2,06,573.9696 kg


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SC(2)-0714 Supercritical airfoil

Max thickness 13.9%

at 37% chord

Max camber 2.5% at

80% chord

Thickness (%) 13.925Camber (%) 1.507Trailing Edge Angle (%) 16.689Lower Surface Flatness 9.397Leading Edge Radius (%) 2.937Maximum Lift (CL) 1.442Maximum Lift Angle-of-Attack (deg) 15Maximum Lift-to-drag (L/D) 37.272Lift at Maximum Lift-to-drag 1.181Angle-of-Attack for Maximum Lift-to-drag

(L/D)4.5


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overnose overside

17 35


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Nose Wheel (4

wheels)

Main Wheel (16

wheels)

Weight 13,611.887 kg 30,626.7457 kg

Diam

eter

32.6867 inches 42.1997 inches

Widt

h

10.0303 inches 14.8034 inches


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NACA 0012

Max thickness 12%

at 30% chord

Max camber 0% at


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GEnx

Length 4.69m

Diamet

er

2.82

m

T/Wratio

5:1

Thrust 284

kN

Bypass 9.6


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General characteristics: Type : Turbofan Length : 4.69 m (184.7 in) Diameter : 2.82 m (111.1 in) Dry weight : 5,816 kg (12,822 lb)

Components: Compressor : Axial, 1 stage fan, 4 stage low

pressure compressor, 10 stage high pressurecompressor

Combustors : Annular Turbine : Axial, 2 stage high pressure turbine, 7

stage low pressure turbine

Performance: Maximum thrust : 284 kN (63,800 lbf) Overall pressure ratio : 41 Thrust-to-weight ratio : approx 5:1


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General characteristics:Crew:6 (2 pilots, 3rd optional, 3

loadmasters)

Capacity (Max. Payload):1,58,620

kg (Disposable fuel 1,50,000kg/

Non-fuel 8,620kg)

Aspect Ratio: 7.75Fuselage Length:58.33 m

Height:16.25 m

Wingspan:65.2878 m

Wing Area:550 sq. m

Thickness-to-Chord Ratio: 37 % of

chordLeading Edge Sweep Back Angle:

27.56

Empty Mass:2,06,573.9696 kg

Maximum Takeoff Mass:

5,44,475.4801 kg

Maximum Landing Mass:

Fuel Transfer Rate:8400 ltrs/min

Powerplant:4 232.6 kN each

Fuel Economy:0.0615 km/ltr

Performance:

Maximum Speed: 892.3 km/hr,Mach 0.835

Cruising speed:768.75 km/hr,

Mach 0.72

Absolute Ceiling: 13,716 m,

45,000 ft

Service Ceiling:10,668 m, 35,000

ft

Range:9,273 km (maximum long

range cruise speed), 4,885.15 km

(with full load)

Ferry range:11,125 km

Endurance: 14.375 hrs


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Documents

Aircraft Design Project – I Presentation