Aerodynamic Design Presentation
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Transcript of Aerodynamic Design Presentation
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AERODYNAMIC DESIGN
HIGH SPEED SUBSONIC BUSINESS JET
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What is a “Business Jet”?“Business jets are turbojet aircrafts weighing less than 100,000 pounds maximum gross Takeoff weight, with wingspans less than 100 feet that are used by companies to conduct their business” [GAO (Government Accountability Office USA), August 2007].
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Motivation for the topicIn today’s corporate world long unexpected intercontinental flights are unavoidable. Though a luxury high speed private jets like our’s are the only solution.
It can also be used by sports persons, cases of medical emergencies etc
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Mission Requirements ➔ Intercontinental(long range)
lightweight medium sized Business Jet
➔ High comfort of passengers
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Technical Specification➔ 10 passengers(executive
arrangements)➔ 4 crew (Pilot, Co-Pilot and 2 flight
attendants)➔ Cruise Range 11000km➔ Cruise Mach no : 0.9
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Mission Profile
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First Weight Estimate
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Second Weight Estimate
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Third Weight Estimation
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Criteria➔ Maximum CL/CD
➔ Maximum CL
➔ Maximum stall angle
➔ Minimum drag➔ Minimum
moment coefficient
Suitable airfoils➢ NACA 64(3)-618➢ NACA 64(4)-421➢ NACA 63(4)-421➢ NACA m9
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NACA 64(3)-618• High Maximum lift coefficient• Very low drag over the range of operating conditions
• Optimized for high speed
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GEOMETRY
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FUSELAGE DESIGN
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FUSELAGE
WIDTH = 2.4 m● 2 seats abreast● 0.7 m executive seat ● 0.8 m aisle width● 0.2 m pressure
cabin structure
LENGTH = 27 m
● Empirical relation● Coefficients from
plots
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WING GEOMETRY
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Wing Area (93.7 m2) ● From gross weight and wing loading
Aspect Ratio = 7.5
Wing span(26.51 m)● using wing area and AR
Taper Ratio (0.2)● to be efficient● reduction in root bending moment● decrease the structural weight
Sweep Angle(34o)● To delay Drag Divergence Root chord length = 5.89 m
Tip chord length = 1.178 m
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TAIL GEOMETRY
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The T-tail configuration
This is mainly to avoid the interference of the flow from aft mounted engine interfering with the tail.
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Horizontal Tail Vertical Tail
Volume Coefficient 0.95
Aspect Ratio 5
Area 25.8
Span 11.38
Root chord length 3.03
Tip chord length 1.517
Volume Coefficient 0.0855
Aspect Ratio 1.2
Area 17.48
Span 4.58
Root chord length 4.08
Tip chord length 3.616
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CONTROL SURFACES➔ AILERON● span =10.604● chord length =0.7068➔ RUDDER● span =4.12● chord length =1.335➔ ELEVATOR● span =10.24● chord length =0.796
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STRUCTURAL LAYOUT
3D DIAGRAMS
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Front View
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Top View
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Side View
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Power Plant Selection
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Engine SizingCriteria
➔ T/W Take-off = 0.269
➔ WO = 27094.28 kg➔ Max Thrust req = (36099.89 * 2) N
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Aircraft Powerplant Maximum Thrust Bypass ratio
Cessna Citation X Rolls-Royce AE 3007 30 KN 4
Gulfstream G550 Rolls-Royce RB.183 Tay
62.8 KN 3.04
Citation longitude Snecma Silvercrest 49 KN 5.9
Dassault Falcon 200lx Pratt & Whitney Canada PW308C
28.6 KN 4.2
Bombardier Challenger 850
General Electric CF34-3B1 turbofans
42 KN 6
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Engine Sizing
After Sizing➔ Length = 2.44m➔ Max Diameter = 1.11m➔ Dry Weight = 626.8 kg
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Inlet➔ Pitot inlet is used taking advantage of
the transonic flow-->RAM EFFECT➔ Vanes are provided at inlet to induce a
vorticity which helps in compression➔ Inner lip radius is greater than outer lip
radius, useful for high angles of attack and sideslip
➔ The capture area was found to be 0.3 m^2
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Drag Polar❖ Equivalent Skin Friction method➔ Cd0 using wetted area➔ e using sweep angle and aspect ratio
❖ Component Build up method➔ component form factor➔ component interference factor
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Induced Drag➔ Leading edge- suction method
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Drag Polar
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Trim AnalysisTrim -> Obtained from equilibrium equations for forces and moments.
The trim obtained is subjected to stability analysis
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Stability Analysis➔ The trim is subjected to small
perturbation analysis and the constraints for CG wrt Neutral Point is obtained (SM--Static Margin)
➔ The most aft location of CG is found to be 14.64m corresponding to a SM of 0.23 .This also determines the maximum elevator deflection.
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CG Estimation
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CG calculations➢ Approximate
Group Method Xcg = 15.86 m Zcg = 2.35 m
➢ Statistical Group Method
Xcg = 14.32 m Zcg = 2.5 m
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Landing Gear - Tricycle/Nosewheel
➔ Stable design➔ Less demanding
on the pilot➔ Small angle of
attack➔ Better visibility
over the nose
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FLAPS - SLOTTED FOWLER TYPE➔ Increased chord length➔ Slot to delay flow separation
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Difficulties faced in Design
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Suggestions for improvement
Winglets Noise Reduction - Nozzle redesign
Fuel Tank
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Are the design requirements met?
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Flight PerformanceThrust Required at cruise 10.38 kN
Vmin (Tr) 238.93m/s
Min Thrust required at cruise 10.152 kN
Vmin(Pr) 181.55m/s
Minimum Power Required at Cruise 2.13 MW
Max Range 13461 km
Sustained Turn Rate 3.51o/sec
Take Off distance 533.56m/s
Total Landing Distance 842.754m
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Flight Performance
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Long Range 11,000 km
Medium Size
Compact Geometry
Light weight 27,094 kg
Comfort