System Definition Review

1. System Definition Review Akshay Ashok, Nithin Kolencherry, Steve Skare, Michael McPeake, Muhammad Azmi, Richard Wang, Mintae Kim, Dodiet Wiraatmaja, Nixon Lange

2. Outline • Re-cap Market Forecasts • Key Design Goals • Progress Update • Constraint Analysis • Concept development process and result • Advanced Technology Concepts • Cabin Layout • Sizing Studies • Overview of Concept • Walk around chart • Conclusion

3. Opportunity Description Create a supersonic transport aircraft that meets the following characteristics: • Mach 1.6-1.8 Cruise Speed • 4000 nm Design range • 35-70 Passengers (Mixed Class) • 3 Pax-mi/lb Fuel Efficiency • Takeoff Field Length < 10000 ft

4. Mission A cost-effective, advanced, high-speed commercial air transport that connects major worldwide hubs Key Design Goals: • Supersonic flights over land (Overpressure < 0.3psf) • IOC in 2020 • Manufacturing capabilities exist • 60 passengers • 4000nm ground range

5. Market Summary • Three regions of focus • Trans-Atlantic • Trans-continental • Inter-Asia • Worldwide Hubs • Los Angeles (LAX) • New York (JFK) • London (LHR) • Dubai (DXB) • Beijing (PEK) • Hub and Spoke Structure • Design Mission

7. Constraint analysis

8. Constraint Analysis • Performance Constraints • 1-g steady flight • M=1.8, H=50000ft, VS=100fpm • Subsonic 2-g maneuver • V=250Kts, H=10000ft • Takeoff and Landing operations from JFK and DXB • Short runway length at JFK • Hot climate at DXB • 2nd segment climb • 3% with 4 engines sensitivity

9. Constraint Analysis

10. Concept selection

11. CONCEPT SELECTION PROCESS BRAINSTORMING • PUGH’s MATRIX (1ST RUN) 3 BASELINE CONCEPTS SELECTED HYBRID CONCEPTS GENERATED FURTHER RESEARCH PUGH’s MATRIX (2ND RUN) FINAL DESIGN

12. Brainstorming Concepts 7 1 8 6 2 5 3 4

13. Pugh’s Matrix

14. Hybrid Concept 1 Engine Location: - Under wing Wing: - Delta - Mid fuselage (height) - Anhedral Control surface: - on wing Sonic boom mitigation: - Hybrid nose design (weak compression waves)

15. Hybrid Concept 2 Engine Location: - Over wing Wing: - Delta -Mid Fuselage - No dihedral/ anhedral Control surface: - Canards - Upper fuselage - Dihedral Sonic boom mitigation: - Nose shaping (F-5 shaped sonic boom demostrator)

16. Hybrid Concept 3 Engine Location: - Under wing inlet - Over wing outlet (similar to YF-23) Wing: - Delta - Bottom fuselage - Dihedral Control surface: - Canards - Top fuselage - Anhedral Sonic boom mitigation: - Gulfstream / NASA Quiet Spike™

17. Aft Arrow Wing Concept • Engine Location: • - Under wing inlet • - Over wing outlet • (similar to YF-23) • Wing: • - Delta • - Bottom fuselage • - Dihedral • Control surface: • - Canards • - Mid fuselage • Sonic boom mitigation: • - aircraft geometry APPLICATION OF SONIC-BOOM MINIMIZATION CONCEPTS IN SUPERSONIC TRANSPORT DESIGN by Harry W, Carlson, Rdymond L. Barger, and Robert J. Muck, LungleyResearch Center, Hdmptolz, Vd. 23665 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JUNE 1973

18. Pugh’s Matrix : 2nd Run

19. Detailed Considerations

21. Supersonix Concept • Further Work: • - Engine placement (over/ under wing) • - Vertical tail selection • - Dihedral/ Anhedral effects (wing/ canard) • - Location of doors

22. Advanced Technology Concepts

23. Boom Shaping : Dihedral • Increase Effective Length • Multi-plane lifting surface • Mitigates Boom overpressure • Potential Issues • Wash out • subsonic lateral instabilities • Low planform area • Lift is reduced • Structural Considerations

24. Boom Shaping :Effective Area Distribution • Smooth area distribution • Gradual lift development • Long chord of wing root • Fuselage diameter morphing • Aircraft length • Engine Nacelle Placement • Area rule • Canards • High dihedral

25. Boom Shaping : Nose Design • Blunt nose • Create strong bow shock • Mitigate subsequent shocks, overpressure • Supersonic Area rule • High wave drag • Nose keel • Alternate option • Unverified results • Material Problems

26. Efficient Supersonic Cruise • Wing Characteristics • High AR, low sweep for efficient supersonic • Laminar flow supersonic wing • Low AR, high sweep for shock mitigation • Need to achieve acceptable trade-off • Active flow management • Attached flow on wing • “Phantom Body” • Artificial area

27. Engines

28. Engines Engines • 107724 lb thrust is needed • Samara NK-321 • Produced by Kuznetsov Design Bureau • Entered service in 1987 • Used on Tupolev Tu-144LL • Noise problem

29. Engine Noise : Solutions Adaptive Cycle Engine (ACE) extra bypass duct on the outside of the engine quiet on take off and landing Significant improvement in subsonic flight Eccentric Exhaust Configuration Decrease the effective perceived noise by 10.5 dB

30. Cabin layout configuration

31. Cabin Layout / Fuselage Design • 7 rows of 2 first class seats, 15 rows of 3 coach class seats • Passenger total: 59 • Crew: 4 (Captain, First Officer, 2 Attendants).

32. Cabin Layout / Fuselage Design • 7 rows First Class x 40” Seat Pitch = 280”15 rows Coach x 36” Seat Pitch = 540”2 Galleys/Restrooms (exits) x 104” = 208”1028” (~90 ft) 90 ft 170 ft

33. Exits Exits Cockpit Crew Seats Cabin Layout / Fuselage Design • Cabin Diameter: 9 feet, Aisle Height: 78” • “Jump seats” for attendants • 4 exits: 2 between FC and coach, 2 overwing

34. Sizing studies

35. Design Mission

36. Sizing Process

38. Component Weights • Used database of 16 existing commercial aircraft • Some differences between our aircraft and those in the database • Horizontal Tail • Delta Wing • Average mass fraction values were corrected based on these differences

39. Component Weights

40. Average Component Weights For 16 Commercial Aircraft

41. Calculated Component Weights (Corrected)

42. Center of Gravity • Utilized Derived Component Weights • Includes All Major Component Weights, Most Minor Weights • Includes: Fuel, Wing, Tail, Canard, Engines, Fuselage, Furnishings, Passengers, etc. • Does Not Include: Baggage, Air Conditioning, Anti-Icing System • Placement was not accurate enough at this stage

43. Center of Gravity Location (at MTOW) ≈ 97 ft • Roughly 57% of the total length of the aircraft • Estimation includes 87% of the take off gross weight of the aircraft • Likely to change, but not significantly

44. Aircraft Summary

45. Blunt Nose Aerodynamically Contoured Skin Arrow-wing Design Top-mounted Canards Area-ruled fuselage for minimum wave drag Dihedral Wing Rear mounted Engines

46. Compliance Matrix

47. References • http://www.nasa.gov/vision/earth/improvingflight/supersonic_jousting.html • Carlson, H.W, Muck, J.R, APPLICATION OF SONIC-BOOM MINIMIZATION CONCEPTS IN SUPERSONIC TRANSPORT DESIGN, June 1973 • F-5 Shaped Sonic Boom Demonstrator’s Persistence of • Boom Shaping Reduction through Turbulence • John M. Morgenstern*, Alan Arslan†, Victor Lyman‡ and Joseph Vadyak§ • Lockheed Martin Aeronautics Company, Palmdale, CA 93599 • AIAA-2005-0012; 43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV • http://www.enemyforces.net/aircraft/mig31.htm • http://www.fighter-planes.com/info/mig31_foxhound.htm • http://www.jet-engine.net/ • Papamoschou, D. Debiasi, M. Conceptual Development of Quiet Turbofan Engines • for Supersonic Aircraft, April 2003

48. questions