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GREYWHALE
- 1. AIRCRAFT DESIGN CONCEPTUAL DESIGN PROJECT ‘GREYWHALE’ – Ground Effect Vehicle SRINIVASA RAGHAVAN – EAU0812382 FAHAD ALI JAIDEV SANKETI – EAU0512252
- 2. Introduction Create a transportation vehicle that is a cross between a ship and an aircraft Having the payloads carrying capacity of a ship and the speed and efficiency of an aircraft. This would require a different mode of flying, a novel body design and a cost estimation that may allow its production.
- 3. Objective Develop the conceptual design of this hybrid aircraft through data Represent our design on Solidworks Check its rough outlook on RDS Perform cost analysis
- 4. Concept- Wing In Ground Effect (WIG) A phenomenon wherein a ‘dynamic cushion’ of air is formed below wings with large wing areas and low ground clearance, due to entrapped wing vortices. This keeps the aircraft afloat, without any effort on the propulsion system.
- 5. Blended Wing Body The integration of the wing and fuselage of an aircraft to allow more payload to be fit into the body, by allowing the in-between volume of the wing and the fuselage to provide the addition in space.
- 6. Design Requirements Mission Profile Parameters Values Range 6000miles Take-off Length 8000ft Payload 1million lb Cruise Velocity 500ft/sec L/D 30 Weight <4millionlb Docking Specially made for aircrafts at necessary port
- 7. Aircraft Comparison Aircraft Type Be-2500 Boeing pelican LUN General Characteristics WIGE aircraft WIGE aircraft WIGE aircraft Country Russia United States of America Russia Role Cargo Cargo Cargo Payload (lb) 2204622 3086471 220000 Length (ft) 379 400 242.12 Wingspan (ft) 411.77 500 144.35 Height (ft) 95.54 18.3 63 Wing Area (ft2) 34272 43000 5900 Aspect Ratio 4.95 5.81 3.75 Max. Takeoff Weight (lb) 5511556 5400000 837757 Mamimum Speed (ft/s) 675 440 501.6 Cruise Speed (ft/s) 410 488.2 410.67 Range (mile) 9942 11508 1243
- 9. Sizing • Initial Sizing • Refined Sizing • Control Surface Sizing
- 10. Initial sizing Range and L/D Ratio Estimation SFC Estimation Empty Weight Ratio Estimation Design Take off Weight Estimation
- 11. Range, SFC and L/D Estimation Range : 5866miles SFC: 8.527*10^-5 (L/D)max: 25.96
- 12. Empty Weight Ratio Estimation
- 13. Design Take-off Weight Estimation at various Trades The estimated Design Take-off Weight:3150988lb Range Trade Payload Trade Composite Material Trade The Wo for the Range 5366 miles is : 3011639.11lb The Wo for the Range 6366 miles is : 3303358lb The Wo for the Payload 1512764 lb is : 4575685lb The Wo for the Payload 512764 lb is : 1678689lb The Wo for using Composite materials is : 2889567lb
- 14. Refined Sizing Detailed Analysis Dropped Payload was considered Different Empty Weight Ratio Table Different Lift to Drag Ratio Calculation
- 15. Empty Weight Ratio Estimation L/D Ratio Using the formula the L/D ratio was obtained as 22.5
- 16. Control Surface Sizing Flap: (2*105*10.5)ft^2 Rudder: (4*140*11.2)ft^2
- 17. Thrust to Weight Ratio Parameters Calculated Values T/W at cruise 0.044 T/W at take off 0.1178 T/W at maximum Mach number 0.219 Optimal T/W : 0.219
- 18. Wing Loading Parameters Calculated Values W/S Stall Speed 23.63lb/ft^2 W/S Take off Distance 43.62 lb/ft^2 W/S Maximum Range 75.514 lb/ft^2 W/S Landing Distance 10.5lb/ft^2 W/S Instantaneous Turn 829.54lb/ft^2 W/S Sustained Turn 130.88lb/ft^2 W/S Climb and Glide 305.84 and 45.029 lb/ft^2 respectively Optimal W/S : 10.5lb/ft^2
- 19. Airfoil Geometry Airfoil selected: NACA 4412 Additional optimization: Shape optimization for better L/D
- 20. Wing Geometry Aspect Ratio Ratio of square of wingspan to wing area. A low aspect ratio is preferred for the main wing, with increased wing area. The value was selected to be 5.12. The canard will have a higher aspect ratio, for better lifting properties. Its aspect ratio is selected to be 9. Taper Ratio Ratio of tip chord length to root chord length. Attain close to elliptical lift distribution. Taper ratio is chosen to be 0.42. Wing twist Geometric twist is used. With low ground clearance, a bit of twist increases L/D. A twist angle of -3o is chosen. Wing incidence Angle of wing with respect to fuselage centerline. This is maintained at 0o to give maximum efficiency to the cushion effect. Wing sweep For the subsonic flow, an aft-sweep angle of less than 10 degrees gives the best aerodynamic properties, but for lateral stability and for naval considerations, a sweep angle of 32 degrees is taken. Dihedral angle Angle of the wings with respect to the fuselage, when seen from the front. An anhedral angle is chosen, to compliment the high-wing design. The angle is taken to be -5 degrees
- 21. Canard Type of canard: Lifting canard Key function: Increase lift Control surface placement Stalls before the wing Key characteristics: High aspect ratio No sweep, taper, incidence and dihedral Provides for 15% of the lift
- 22. Wing Configuration Main Wing: High wing configuration with blended wing body design Anhedral angle has a new configuration Canard: Mid wing configuration Not placed in line with the engine to avoid wake ingestion Wing tips: Drooped wing tips are used Provide better reach and cushion effect Control Surfaces and high lift devices: Flaps on main wing Drag rudders on canard for 3-D direction control No ailerons
- 23. Special Considerations Structures Crashworthiness Maintainability Power Augmented Ram Flying Conditions Docking
- 24. Structures, Maintainability and Crashworthiness Structure: Keelson Skin clearance of 5 inches Crashworthiness Scarfed firewall Hull Like Front Dead rise Angle: 𝑉 2 − 100 = 150 Maintainability Difficult. Engine access doors, pilot entrance, passenger entrance may have common access point. Easy for engines.
- 25. Additional Considerations Power Augmented Ram (PAR) Angled engine exhaust nozzles, for additional lifting properties. Active on two engines. Variable angles capability in all. Flying Conditions Ground clearance is half of wingspan. This gives a cruising altitude of 210 feet to take advantage of WIG effect. Docking Specially constructed on the port to allow cargo loading, passenger entrance, MRO purposes. Dimensions: 500 f x 450 ft x 70 ft.
- 26. Fuselage Sizing Fineness Ratio: 7 Fuselage Length Estimation: 417.26ft (Table)
- 27. Propulsion Engine Selection Inlet Selection Nozzle Selection Fuel Tank Fuel
- 28. Engine Selection Piston-prop Turboprop Turbofan Turbojet Types of Engines Engine Category Selection Turbofan for its low fuel consumption and high thrust
- 29. Engine Selection CF6-80C2 Engine manufactured by General Electrics Characteristics Components LPC 1 fan 3 primary stages HPC 14 primary stages 5 stages with variable stator vanes HPT 2 primary stages LPT 5 primary stages Max diameter (inches) 106 Length (inches) 168 Dry weight (lb) 9.480 - 9,860 Overall pressure ratio 27.1 - 31.8 Bypass ratio 5 - 5.31
- 30. Scale Factor Required Thrust : 371469.79lbf Current Thrust : 236000lbf Scale Factor: 1.57 New Length : 16.785ft New Diameter : 11.07 New Weight : 12370lb
- 31. Inlet Selection and location Selection Pitot Inlet Location Over Wing
- 34. Fuel Tank And Fuel Selection Fuel Tank Integral Tank Bladder Tank Fuel Aviation bio-fuel
- 35. Fuel Tanks
- 36. Subsystems Hydraulic Systems Flaps Fly by Wire System Drag Rudders A.P.U CRJ-200 Avionics
- 37. Crew station Passengers and Payload Cabin layout Cockpit Seat Configuration Passengers Seating Configuration Loading bay doors
- 38. Crew Station Grazing angle: 300 Overnose angle: 4.90 Crew members: 3 officers 12 others enlisted Cockpit length: 16.41ft
- 39. Passengers First Class : 2-3-2 First Class Seats: 35 Economy Class: 2-3-3-3-2 Economy Class seats: 265 Total Seats: 300
- 40. Cargo Provisions LD-3 Containers Number of containers: 60 Volume : 35000ft^3 Cargo volume per passenger: 11ft^3 The cargo volume is thrice the volume of C-5 outsized cargo aircraft, giving it a cargo bay width of 30 feet, 15 feet height and a length of 150m. The cargo loading is done from the bottom part of the aircraft, through loading bay. Hinge Line For Cargo Door
- 41. Stability and Control Calculation of centre of gravity Group Weights Stability
- 42. Group Weights Parameters Values Wing Weight 386903.92lb Fuselage Weight 115372lb Engine Control Weight 500lb Starter System Weight 406.39lb Nacelle Systems Weight 9096.73lb Fuel Systems Weight 1926.75lb Instruments Weight 2258.52lb Flight Controls Weight 8636.0416lb APU Weight 1650lb Hydraulics Weight 46.41lb Electrical Weight 2016.163lb Avionics Weight 1915.62lb Air Conditioning Weight 167.45lb Anti-Icing Weight 4235lb
- 43. Centre of Gravity Crew, passenger and payload Crew and full fuel Crew and no fuel Crew, passenger and no payload
- 44. Stability Longitudinal Stability Lateral Stability Spinning
- 45. Longitudinal and Lateral Stability Parameter Value 𝑿 𝒏𝒑 207.433ft 𝑪 𝒎 −0.746/𝑟𝑎𝑑 Parameter Value 𝑪 𝒏𝜷 0.153/rad 𝑪𝒍𝜷 −0.214/rad Longitudinal Stability Lateral Stability
- 46. Performance and Flight Mechanics Parameter Value ( 𝑇 𝑊 )SLF 0.139 VSLF 192.23𝑓𝑡/𝑠𝑒𝑐 𝑉 𝑚𝑖𝑛𝑖𝑚𝑢𝑚 𝑡ℎ𝑟𝑢𝑠𝑡 𝑜𝑟 𝑑𝑟𝑎𝑔 379.233𝑓𝑡/ sec 𝑜𝑟 141.39𝑓𝑡/𝑠𝑒𝑐 𝑉𝑏𝑒𝑠𝑡 𝑟𝑎𝑛𝑔𝑒 501.99𝑓𝑡/𝑠𝑒𝑐 𝐶𝐿 𝑏𝑒𝑠𝑡 𝑟𝑎𝑛𝑔𝑒 0.2522 𝐷 𝑏𝑒𝑠𝑡 𝑟𝑎𝑛𝑔𝑒 206292.0331𝑙𝑏 𝑉𝑓 92.829𝑓𝑡/ 𝑠𝑒𝑐 𝑆 𝑎 7776.68𝑓𝑡 𝝁 0.78 Balanced Field Length 6950ft 𝑉𝑎𝑝𝑝𝑟𝑜𝑎𝑐ℎ 109.7𝑓𝑡/𝑠𝑒𝑐 𝑉𝑓𝑙𝑎𝑟𝑒 103.8𝑓𝑡/𝑠𝑒𝑐
- 47. Views- Auto CAD Front ViewTop ViewSide View
- 48. Views- Solid Works Front ViewTop ViewSide View
- 49. Isometric Views
- 50. RDS- Results Front ViewTop ViewSide View
- 51. Cost Analysis Life Cycle Cost Cost Estimation Method Aircraft Economics Cost Prediction
- 52. Life Cycle Cost RDT&E 10% Special Construction 10% Production 40% O&M 40% LCC Breakdown RDT&E Special Construction Production O&M
- 54. Aircraft Economics Cargo and passengers – dual source of income DOC is 3-4 cents per mile Higher IOC of 40-50% Load factor of 80-90% Ticket sales: 20% in first class, 80% in economy. Breakeven analysis shows 20 aircrafts to pay off R&D costs
- 55. Cost Prediction Modified DAPCA IV Cost Model: RDT&E costs + Flyaway costs = $580.48 million Total Aircraft Cost = 100/50(580.85) = $1161.7 million = $1.161 billion.
- 57. Conclusion Therefore, a conceptual design of ‘GreyWhale’ – a large WIG aircraft – is completed. Its functional, payload, aerodynamic and structural requirements have been selected. This complies with our mission and design requirements. All other special considerations, safety and cost estimation have also been predicted.
- 58. THANK YOU FOR YOUR PATIENCE Questions?