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

Company LOGO 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

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

Company LOGO 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

Company LOGO 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

Company LOGO

Company LOGO CONSTRAINT ANALYSIS

Company LOGO 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

Company LOGO Constraint Analysis

Company LOGO CONCEPT SELECTION

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

Company LOGO Brainstorming Concepts

Company LOGO 1st run CONCORDE 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 s Pugh’s Matrix

Company LOGO 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

Company LOGO 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

Company LOGO 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

Company LOGO 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 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

Company LOGO 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 s322 Pugh’s Matrix : 2 nd Run

Company LOGO 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

Company LOGO

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

Company LOGO ADVANCED TECHNOLOGY CONCEPTS

Company LOGO 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

Company LOGO 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

Company LOGO 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

Company LOGO 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

Company LOGO Engines

Company LOGO Engines – lb thrust is needed – Samara NK-321 Produced by Kuznetsov Design Bureau Entered service in 1987 Used on Tupolev Tu-144LL Noise problem

Company LOGO 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

Company LOGO CABIN LAYOUT CONFIGURATION

Company LOGO 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).

Company LOGO 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)

Company LOGO 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

Company LOGO SIZING STUDIES

Company LOGO Design Mission

Company LOGO Sizing Process

Company LOGO AttributesValues W 0 Design lb W e Design lb W f Design lb T sl Required lb f Wing Area3340 ft 2 Design Range4700 nm AR2.1 W 0 /S85 lb f /ft 2 T sl /W 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

Company LOGO 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

Company LOGO Component Weights

Company LOGO Average Component Weights For 16 Commercial Aircraft

Company LOGO Calculated Component Weights (Corrected)

Company LOGO 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

Company LOGO 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

Company LOGO AIRCRAFT SUMMARY

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

Company LOGO Compliance Matrix RequirementsTargetThresholdRevised on 3/3Requirement Units Take off field length ft Landing field length ft Door height above ground810 ft Turnaround time0.51 hr Still air range nm Number of passenger605059people Cruise Mach number Mach Cabin volume per pax pax/[ft^3/pax] Operating cost $/ASM Cruise Altitude ft Cruise Efficiency lb fuel/pax mi Sonic boom overpressure lb/ft^2 Cumulative certification noise6080 dB Stall Speed kts COTs8050 % Second Segment climb gradient %

Company LOGO References 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 AIAA ; 43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV Papamoschou, D. Debiasi, M. Conceptual Development of Quiet Turbofan Engines for Supersonic Aircraft, April 2003

Company LOGO QUESTIONS