design of the subsonic passenger aircraft
TRANSCRIPT
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DESIGN OF THE SUBSONIC PASSENGER AIRCRAFT
ACHUMON R 98308101302
BENADICT BENSIGER S S 98308101016
THIRUMURUGAN S 98308101053
VARKIS NIRMAL L 98308101301
Submitted by
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Abstract
The purpose of the project is to design subsonic passenger aircraft.
The aircraft will possess a sweep back low wing, multi-bogey landing gear and a conventional tail arrangement.
It have a wide body configuration to provide sufficient seating capacity.
It must possess turbofan engines to provide the amount of speed, range and fuel economy for the operation.
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INTRODUCTION• We propose to design subsonic passenger aircraft.• It’s Mach number 0.8 and altitude 13000m.• Its range will be 13,000km with a full payload.• This will comfortably accommodate from 300-400 passengers.• Maximum take off weight 61600kg.• Other features of the design include swept back wing
configuration with winglets, split type flaps and very light weight structure.
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COMPARATIVE STUDY DIMENSION SPECIFICATION
WEIGHT SPECIFICATION
POWERPLANT SPECIFICATION
PERFORMANCE SPECIFICATION
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Selection of Main Parameters
Airfoil SelectionNASA SC(2)-0412
Wing ConfigurationSwept back, low wings
Landing Gear SpecificationRetractable multi-bogey type
Location of CG
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GRAPHS
Mach number (M) vs Coefficient of Lift (CL)Mach number (M) vs Maximum L/DVelocity (V) vs Weight (W)Velocity (V) vs Wing loading (W/S)Mach number (M) vs Specific fuel consumption
(SFC)Coefficient of Drag (CD) vs Coefficient of Lift (CL)Velocity (V) vs Range (R)Velocity (V) vs Aspect ratio (AR)Velocity (V) vs Altitude (h)Angle of attack (α) vs Coefficient of lift (CL)
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Optimum valuesSl. No. Design parameters Values
1 Mach number 0.85
2 Velocity 253.8m/s
3 Coefficient of lift 2.82
4 Coefficient of drag 0.15
5 Maximum L/D 18.4
6 Weight 223,465kg
7 Wing loading 713.4
8 Specific fuel consumption 0.3472
9 Range 13,038km
10 Aspect ratio 8.586
11 Altitude 13,052m
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Mission profile
Landing
Glide
Take off
Climb
CruiseLoiter
44 55
22 33
1100
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Take-off weight estimationTotal take off weight is divided into fuel weight, weight of crew, weight of payload, and empty weight.
W0 = Wfuel + Wcrew + Wpayload + Wempty
The fuel and empty weights are expressed as,
This can be solved for W0, we get,
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Empty weight fraction
Fuel weight fraction
Maximum Take-Off Weight (W0) = 616,000kg.
Weight of the Fuel (Wf) = 210,424kg
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Engine selection
Engine : Trent 772B-60 Thrust : 71,100lb Bypass ratio : 5.0 Inlet mass flow : 2030lb/sec Fan diameter : 97.4in Length : 154in
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Properties of selected Aerofoil: NASA SC(2)-0412
Properties of aerofoil NASA SC(2)-0412
Thickness 12.00%Camber 1.30%Trailing edge angle 3.6o
Lower flatness 4.00%Leading edge radius 2.30%Max CL 1.177
Max CL angle 15
Max L/D 23.492Max L/D angle 5Stall angle 5Zero-lift angle -2.5
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NASA SC(2)-0412
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Effect of flap
Coefficient of lift with Angle of attack with and with out flap.
Coefficient of lift with coefficient of drag with and with out flap.
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Wing configurationSweep back, low wing is selected for our
design.
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THE MAIN WING DESIGN PARAMETERS CAN BE IDENTIFIED UNDER FOUR HEADINGS:
performance requirementsflying qualitiesstructural frameworkinternal volume
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Horizontal and vertical tail:
Fuselage mounted tail is used.
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The general drag equation is given by,
Calculation of drag
Drag, D= 34936N
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Take off distance
The equations to be used to determine the effect of the take-off criterion is shown below:
Take-off distance is 2,700m to 3,200m.
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Landing distance
The approximate equation to determine ground run in landing can be rewritten as shown below:
Landing distance is 1,900m to 2,100m.
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Center of gravity
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Side view
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Front view
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Top view
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Conclusion
Thus we done the design project successfully. Design is a fine blend of science, creativity, presence of mind
and the application of each one of them at the appropriate time. The scientific society always looks for the best product design. This involves the strong fundamentals in science and
mathematics and their skilful applications, which is a tough job endowed upon the designer.
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THANK YOU