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

2. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com 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

6. Company LOGO www.company.com

7. Company LOGO www.company.com CONSTRAINT ANALYSIS

8. Company LOGO www.company.com 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 – 2 nd segment climb 3% with 4 engines

9. Company LOGO www.company.com Constraint Analysis

10. Company LOGO www.company.com CONCEPT SELECTION

11. Company LOGO www.company.com BRAINSTORMING PUGH’s MATRIX (1 ST RUN) 3 BASELINE CONCEPTS SELECTED HYBRID CONCEPTS GENERATED FURTHER RESEARCH PUGH’s MATRIX (2 ND RUN) FINAL DESIGN

12. Company LOGO www.company.com Brainstorming Concepts 1 2 3 4 5 6 7 8

13. Company LOGO www.company.com 1st run CONCORDE12345678 D A T U M SONIC BOOM++s++s++ SUBSONIC NOISEssss++s+ TURN AROUND TIMEsssss++s AIRPORT COMPATIBLEs--s---- SAFETYssss+ss+ EASE OF MANUFACTURE++-+++-s CABIN VOLUME++sssss+ COST++-+s+-s MOVING PARTS+--+++-- AESTHETICSs--sss-s +54045524 -03501152 s53454434 Pugh’s Matrix

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

15. Company LOGO www.company.com 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) Hybrid Concept 2

16. Company LOGO www.company.com 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™ Hybrid Concept 3

17. Company LOGO www.company.com APPLICATION OF SONIC-BOOM MINIMIZATION CONCEPTS IN SUPERSONIC TRANSPORT DESIGN by Harry W, Carlson, Rdymond L. Barger, and Robert J. Muck, Lungley Research Center, Hdmptolz, Vd. 23665 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JUNE 1973 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 Aft Arrow Wing Concept

18. Company LOGO www.company.com 2nd run AFT ARROW WING CONCEPTHYBRID CONCEPT 1HYBRID CONCEPT 2HYBRID CONCEPT 3 D A T U M SONIC BOOM--- SUBSONIC NOISEs+s CONTROL SURFACES-ss TURN AROUND TIMEs++ AIRPORT COMPATIBLE++- SAFETYs+- EASE OF MANUFACTURE-s- EMPTY WEIGHT++s COST--- +251 -425 s322 Pugh’s Matrix : 2 nd Run

19. Company LOGO www.company.com DESIGN CRITERIA DETAILED DESCRIPTION SONIC BOOMgeometryaltitudeweightwetted areaaspect ratiofrontal areainduced drag control surface effects SUBSONIC NOISEengine placementnoise mitigationtype of engine CONTROL SURFACES types of control surfacesstatic stabilitynumber location of control sufaces airport compatibilitycomplexity size of control surfacesweight TURN AROUND TIME # of passenger doors# of service doorspreflight checks AIRPORT COMPATIBLE location of control sufaceslocation of doorsgeometryfuel bay location engine placement SAFETYengine placementfuel bay locationlanding gear vertical stabilizer osciallations emergency exitsstabilitydebrispreflight EASE OF MANUFACTUREmoving partsmaterials usedgeometrycosts EMPTY WEIGHT# of enginesmaterials used# of landing gearwing size # of moving parts COSTprocurementoperationmanufacturemaintenancecrew Detailed Considerations

20. Company LOGO www.company.com

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

22. Company LOGO www.company.com ADVANCED TECHNOLOGY CONCEPTS

23. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com Engines

28. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com CABIN LAYOUT CONFIGURATION

31. Company LOGO www.company.com 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. Company LOGO www.company.com 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 170 ft (~90 ft)

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

34. Company LOGO www.company.com SIZING STUDIES

35. Company LOGO www.company.com Design Mission

36. Company LOGO www.company.com Sizing Process

37. Company LOGO www.company.com AttributesValues W 0 Design284000 lb W e Design124000 lb W f Design143000 lb T sl Required108000 lb f Wing Area3340 ft 2 Design Range4700 nm AR2.1 W 0 /S85 lb f /ft 2 T sl /W 0 0.38 Cruise Mach #1.8 Maximum Mach #2.0 SFC cruise0.94 1/hr Supersonic (L/D) max 9.2 Supersonic (L/D) cruise 7.9 Subsonic (L/D) max 10 Subsonic (L/D) loiter 10

38. Company LOGO www.company.com 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. Company LOGO www.company.com Component Weights

40. Company LOGO www.company.com Average Component Weights For 16 Commercial Aircraft

41. Company LOGO www.company.com Calculated Component Weights (Corrected)

42. Company LOGO www.company.com 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. Company LOGO www.company.com 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. Company LOGO www.company.com AIRCRAFT SUMMARY

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

46. Company LOGO www.company.com Compliance Matrix RequirementsTargetThresholdRevised on 3/3Requirement Units Take off field length8400100008000ft Landing field length8400100002800ft Door height above ground810 ft Turnaround time0.51 hr Still air range50004000 nm Number of passenger605059people Cruise Mach number21.61.8Mach Cabin volume per pax655043.13033982pax/[ft^3/pax] Operating cost $/ASM Cruise Altitude500004000050000ft Cruise Efficiency 0.30.6lb fuel/pax mi Sonic boom overpressure0.3 0.8lb/ft^2 Cumulative certification noise6080 dB Stall Speed kts COTs8050 % Second Segment climb gradient2.62.43%

47. Company LOGO www.company.com 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. Company LOGO www.company.com QUESTIONS