Poorvi Kalaria Roman Maire Andy Grimes Motohide Ho Tara Palmer Greg Freeman Vicki Huff Nick Gurtowski Jack Yan

1. Poorvi Kalaria Roman Maire Andy Grimes Motohide Ho Tara Palmer Greg Freeman Vicki Huff Nick Gurtowski Jack Yang Sanjeev Ramaiah

2. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

3. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

4. Mission Objectives • Design an aircraft with supersonic capabilities that is able to link major business city pairs. • Compete with other existing aircraft on the market. Aerion Corporation SBJ Dassault Aviation HISAC Lockheed Martin QSST Sukhoi S-21

5. Conceptual Design Review • First and Business class seating • Prime design focuses are cruise Mach number and cruise • efficiency • Will fly only overseas due to FAR36 and to avoid the ill • effects of sonic boom overland • Around 248 units will be sold in order to operate • profitably between 24 city pairs • Still air range is 5450 nmi. • Design cruise altitude is 50,000 ft. • Design maximum cruise Mach number is 1.8

6. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

7. Concepts of Operation • Transpacific City Pairs • Transatlantic City Pairs

8. Concepts of Operation • Meeting the customers needs: • Luxurious cabin space • Improved seating space compared to the Concorde • High quality entertainment and communication capabilities for improved productivity during flight • Shorter travel time • Payload and Passenger capacity: • 4 Crew members (180 lbs) • 49 (180 lbs) • 53 pieces of luggage (50 lbs) • Extra Payload 10,000 lbs • Total Payload = 22,190 lb

9. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

10. Major Design Requirements • Customer Attributes

11. Major Design Requirements • Engineering Requirements

12. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

13. Selected Aircraft Concept Delta wing with double sweep, fits inside Mach cone of 60º, root chord of 95ft Canards for stability of the aircraft Possible Winglets for compression lift, AR = 1.9 Placed >5ft from door

14. Selected Aircraft Concept Main Gears will fold inward to fuselage 4 Engines required to provide enough thrust. Low Wing Configuration Inlet to engines are variable for supersonic and subsonic flight Tricycle Landing gear configuration

15. Selected Aircraft Concept Fuselage designed according to Sears Haack Body(area rule) Nose Gear Nose has a slight droop for aerodynamics Exhaust point for APU, approx 2ft in diameter

16. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

17. Aircraft Design Mission • Design Mission Worst Case Scenario

18. Aircraft Design Mission • Clarification on the transonic regime (acceleration and deceleration) • During cruise (50,000 ft) • D/W = 0.105 • During transonic acceleration (30,000 ft) • D/W = 0.085

19. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

20. Sizing Results • MATLAB sizing approach • Consists of functions for different flight segments (i.e. climb, cruise, etc.) • No variation from aircraft design mission • Assumes no range descents/deceleration • Approach is included in landing • Functions were set up for thrust and drag • Iterative “while” loop to solve for TOGW, fuel weight, empty weight

21. Segment Functions • Takeoff • Uses combination of takeoff parameters to determine weight fraction (sfc, bfl) • Climbs • Does not physically compute drag as weight changes • Simple equations for subsonic and supersonic climb • Subsonic weight ratio: 1.0065-0.0325*M • Supersonic weight ratio: 0.991-0.007*M-0.01*M^2 • Cruise • Segmented approach dividing cruise into 500 segments recalculating weight fraction in each loop • Output final cruise weight fraction • Incorporates Breguet Range equation

22. Segment Functions cont’d • Loiter • Function of current weight and current wing area • Incorporates Breguet Endurance equation • Landing • Simple constant fraction of 0.995 used based on past numbers • Sufficient for conceptual design

23. Engine Modeling • ONX and OFFX • Turbofan with mixed exhaust (no A/B) • Datum from Raymer Appendix E.1 • Iterated with different: • Compressor & Fan Pressure Ratios • Bypass Ratio • Output: • TSFC, thrust as functions of altitude, Mach • TSFC as a function of altitude, Mach, partial thrust

24. Important Constants

25. Weight Fractions

26. Final Weights W0 = 467,000 lbs Wf= 226,000 lbs We = 218,000 lbs W0 = 453,000 lbs Wf = 219,000 lbs We = 209,000 lbs

27. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

28. Objective & Variables • Objective: • Minimize Takeoff Gross Weight, W0 [lb] • Variables: • Wing Loading, W0/S [lb/ft2] • Center Point: 110 lb/ft2 • 90 lb/ft2, 100 lb/ft2, 110 lb/ft2, 120 lb/ft2, 130 lb/ft2 • Thrust-to-Weight Ratio, T/W0 • Center Point: 0.45 • 0.35, 0.45, 0.55

29. Constraints • Five Constraints • Takeoff Distance = • Landing Distance = • Climb Gradient, 2nd Segment Climb = • Fuel Efficiency = • Specific Power, 2g Maneuver =

30. Constraints • Five Constraints • *Take-off Distance = dTO ≤ 10,000 ft • Landing Distance = dL≤ 10,000 ft • Climb Gradient, 2nd Segment Climb = CGR ≥ 3% • *Fuel Efficiency = η ≥ 3 pax-mi/lb-fuel • Specific Power, 2g Maneuver = PS ≥ 0 ft/s

31. Sizing Matrix

32. Carpet Plot with Constraints Best W0/S and T/W0

33. Conclusions from Carpet Plot *Meet all constraints except fuel efficiency. • Initial Values • Carpet Plot Values • W0/S • 107 lb/ft2 • T/W0 • 0.45 • WT0 • 467214 lb • Best W0/S • 115 lb/ft2 • Best T/W0 • 0.45 • Optimized WT0 • 452642 lb

34. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

35. Aircraft Description • Fuselage Length = 198’ • Height of Airplane • with landing gears down = 33’ • Span of Delta Wing = 103.17’ • AR = 2.6 with Wingtips Up • AR = 1.9 with Wingtips Down

36. Aircraft Description • Cabin Length = 90’ • Max Diameter = 8.5’ • Tail Diameter = 2’ • 2 Class Configuration • of First and Business

37. Aircraft Description

38. Aircraft Description

39. Aircraft Description Cabin Bin Volume = 111.03 ft3 Cabin Bin Vol. / PAX = 2.3 ft3 Cabin Height from Seat = 1.25 ft

40. Aircraft Description • First Class Seat Pitch = 46” • Business Class Seat Pitch = 42” • 1 Boarding Door (1R) • 2 Emergency Exits • 2 Lavatories • Galley located aft of Business Class

41. Conceptual Design Review Mission Objectives Concept of Operations Major Design Requirements Aircraft Concept Design Missions Sizing Results Carpet Plot Summary Aircraft Description Aerodynamics Sonic Boom Propulsion Structures Weight/Balance Stability and Control Cost Summary

42. Aerodynamics Details • Choice of Airfoil • Airfoil from research paper: • Optimum airfoil thickness distribution for minimum drag at M = 1.75 ≈ 1.8 • Reduction of 10% of the drag from the wing during cruise. • 3% thickness due to structure constraint • Insert airfoil profile from optimum drag airfoil

43. Aerodynamics Details • Compression Lift • From the B-70 data: • L/D improvement of • ΔL/D = 0.4 • ≈ 30 % of lift generated by compression

44. Aerodynamics Details • Supersonic Aerodynamics • From Raymer’s approximation of lift curve slope for different taper: • The airfoil lift curve slope has a value of CLα = 0.0423 • 3.3o Angle of Attack needed if compression lift not used • 1.5o Angle of Attack with use of compression lift • The induced drag is reduced by the wave drag is increased. Further analysis needed to make sure it is beneficial at speeds as low as M =1.8

45. Aerodynamics Details • Lift curve at subsonic regimes • Lift built up method • Assumptions: • Inner part of the wing behaves as a delta wing (mostly vortex flow generated lift) • Outer part of the wing behave as a regular wing (mostly airfoil generated lift) Take off

46. Aerodynamics Details • High Lift devices • Delta wing high lift devices research (Japan) • Trailing edge span wise jet blowing used to increase the CL of delta wings at low speeds by avoiding flow reversal. • Increase of CL ≈ 0.2

47. Drag Prediction Approach • Three types of drag • Parasite drag • Induced drag • Wave drag • Subsonic drag • Parasite drag (zero- lift drag) • Skin friction, Pressure, Interference drag coefficients • Miscellaneous drag • Induced drag • Induced drag coefficient

48. Drag Prediction Approach • Method for estimation of subsonic drag • Parasite drag • Wings • Fuselage • Nacelles • Induced drag

49. Drag Prediction Approach • Method for estimation of supersonic drag • Parasite drag • No adjustment for form factor and interference • Induced drag

50. Drag Prediction Approach, Focus Upon Wave Drag Approach: • Difficulties and Constraints- - Limited resources in regarding to the fact that each company uses many proprietary methods that are not available to the general publics. - Difficult to obtain a very accurate wave drag model in a short period of time. - CFD does not allow simple and prompt prediction of the required aerodynamic data. • Approach- -With limited resources and time as constraints, an approach simpler than CFD analysis and as accurate as possible must be taken.