1. Logan Waddell Morgan Buchanan Erik Susemichel Aaron Foster Craig Wikert Adam Ata Li Tan Matt Haas 1

2. Outline I. Mission Statement II. Market and Customers a. Market size b. Customer Benefits / Needs III. Competition IV. Concept of Operations a. Representative City Pairs b. Payload / Capacity c. Design Mission V. System Design Requirements a. Design Requirements b. Benchmarking VI. Technologies / Advanced Concepts VII. Initial Sizing 2

3. Mission Statement  To design an environmentally responsible aircraft that sufficiently completes the “N+2” requirements for the NASA green aviation challenge.  “N+2” Goals ○ Burn 50% less fuel burn ○ Cumulative -42 dB noise reduction (Approach, Landing, Taxi) ○ 75% reduction in LTO nitrogen oxide emissions 3

4. Customer Needs / Benefits  NASA ○ “N+2” goals  Airlines  General Public 4 Airport Noise levels

5. Market / Customers *Boeing 5 Twin Aisle - Value ($B) ~3,600 Twin Aisle – 7,100 new airplanes Boeing projects the worlds fleet to double by 2029

6. Market / Customers 6 *Boeing Steady increase in RPK since 1977, ~ 5% annually Largest Markets: Asia-Pacific, North America, Europe

7. Competition  Similar size aircraft: ○ Boeing 767-300, 757-300, 787 ○ Airbus A330-200  High speed rail ○ Bullet trains 7 Boeing 757 and 767

8. CONOPS - City Pairs  Mission design represents popular routes Examples Routes Great Circle Distance Passengers / Year ____________________________(nm)__________________________  Domestic range requirement of 3200 nm based on: MIA to SEA facing 65 kts headwind FAR Reserves LondonNew York29991609337 MiamiSeattle2363 N/A New YorkSan Francisco2224909514 Los AngelesNew York21451697593 MiamiNew York948955838 AtlantaNew York659935265 ChicagoNew York6411182326 Las VegasLos Angeles205924732 BostonNew York162988976 8

9. Runway Length *MIT AirportRunway lengths (ft) JFK14572 ORD13001 LAX12091 SFO11870 LHR12799 LAS14510 MIA13000 ATL11890 BOS10083 SEA11900 9

10. Aircraft Payload / Passenger Capacity  250 Passengers 180 lb/passenger Baggage 50 lb/passenger On board Baggage 15 lb/passenger  7 Crew Members 180 lb/crew Baggage 30 lb/crew W payload = 61250 lbs W crew = 1470 lbs 10

11. Design Mission 11

12. Typical Operating Mission Typical Design Missions Aircraft QualitiesAircraft LimitationsTypical Design Mission Range4,000 nm750 nm City PairsSeattle to MiamiChicago to New York Passengers250212 Cruise Altitude35,000 ft30,000 ft Reserve Segments200 nm100 nm Takeoff Weight268,000 lbs243,100 lbs Mach Number0.8 12

13. Design Requirements Compliance Matrix RequirementUnitTargetThresholdCurrent Rangenaut. miles40003600- Payloadpax250230250 Cruise Mach #-0.80.760.8 Runway Length (Takeoff)ft70009000- Runway Length (Landing)ft60006500- Emissionsg/kN thrust1522- Noise (Cum.)dB-42-32- Fuel Burn (SFC)-Cruiselb/(lbs*hr)0.30.45- 13

14. Design Requirements Noise (below stage 4) -42 dB LTO NO x Emissions (below CAEP 6) -75% Performance: Aircraft Fuel Burn -50% Performance: Field Length -50% ERA N+2 Requirements  Noise prediction/reduction technologies for airframe/propulsion systems  Emissions-reduction technologies (mainly NO x )  Alternative Fuel Usage  Improved vehicle performance from: Lightweight, durable structures High-lift aerodynamics Higher bypass ratio engines NASA Subsonic Fixed Wing Project Goals: 14

15. Benchmarking Max Passengers OEW (lb) Max Takeoff Weight (lb) Max Payload (lb) Usable Fuel (lb) Cruise Mach # Max Field Length (ft) Max Range (nmi) Boeing 757-200PF279142,350270,00038,20079,9800.8013,5004,750 Boeing 767-200ER255181,610395,00078,500161,7380.8013,0006,385 Boeing 777-200LR301320,000766,000141,000320,8630.8414,0009,395 Airbus A321-200220103,527187,39354,00051,3700.7915,0003,200 Airbus A330-200380264,845480,607115,01297,5300.8215,0007,250 Info on Boeing aircraft from boeing.com Info on Airbus aircraft from airbus.com 15

16. Technologies/Advanced Concepts  Fuel Burn  Spiroid winglets  Advanced engine concepts  Noise  Landing gear  Emissions  Less fuel burn 16

17. Technologies/Advanced concepts  Winglets ○ Blended ○ Spiroid ○ Multi-Winglets 17

18. Geared Turbofan Engine  Pratt & Whitney currently has a line of geared turbofan engines called the PurePower family. Developing advanced GTF for Airbus and Boeing next gen narrow body replacement aircraft.  Geared Turbofan allows fan to operate at lower speeds while compressor and turbine operate at high speeds.  Provides 12%-15% improvement in fuel burn range, 50% NOx emissions reduction, and 20 dB decrease from CAEP noise standards 18

19. Affordable Large Integrated Structures  Eliminates structural discontinuities and fastened assemblies  Reduction in part count  Lower manufacturing time and cost 19 Northrop Grumman

20. Landing Gear Fairings  Reduces the noise in the mid and high frequency domain compared to the plain landing gear configuration up to 4.5 dB  Reduces vortex shedding due to bluff-body nature of nose and main landing gear Northrop Grumman 20

21. Hybrid Laminar Flow Control 21 Active drag reduction technique Design of the suction surface Chambers underneath the perforated skin Applied to the vertical and horizontal tail reduces drag by 1% *Clean Sky

22. Composite Materials  Lighter weight ○ High strength to weight ratio ○ Reduction of overall weight 20% or more  Stronger ○ Graphite/epoxy composite ○ Greater resistance to damage from cyclic loading  Hybrid ○ Addition of fiberglass or kevlar ○ Creates greater fatigue toughness ○ Impact resistance 22

23. Sizing Using MATLAB to create a comprehensive sizing code based on first order method from Raymer text Empty weight prediction based off of Raymer database (Table 3.1) Equation Used: W e /W 0 =A*W 0 C *K vs Fuel weight prediction based on drag and fuel burn predictions Climb, Landing, Warmup and Takeoff fractions used historical data Cruise fraction used Breguet range equation: exp(-R*C/(V*L/D)) Loiter fraction used endurance equation: exp(-E*C/(L/D)) L/D prediction Equation Used: L/D = 1.4*AR+7.1 23

24. Aircraft Database Published Information (from Jane’s All the Worlds Aircraft and Boeing.com) Boeing 767-200ERAirbus A330-200 Range6,545 [nmi]6,750 [nmi] Takeoff Gross Weight395,000 [lb]507,050 [lb] Empty Weight (OWE)184,400 [lb]263,075 [lb] Fuel Weight159,920 [lb]186,255 [lb] Total Fuel capacity23,980 [gal]36,750 [gal] Boeing 767-200ERAirbus A330-200 24

25. Sizing Code Predictions ActualPrediction% Error Gross Takeoff Weight 395,000 [lb]408,264 [lb]3.35 Empty Weight Fraction.46684.46980.63 L/D (cruise) 1818.32.22 ActualPrediction% Error Gross Takeoff Weight 507,050 [lb]365,624 [lb]-27.89 Empty Weight Fraction.51883.47295-8.80 L/D (cruise) N/A Boeing 767-200ERAirbus A330-200 The initial sizing calculations prove to be mostly accurate on both of the baseline aircraft 25

26. Our Design Predictions Prediction Gross Takeoff Weight267,365 [lb] Empty Weight128,848 [lb] Empty Weight Fraction.48192 26

27. Summary and Next Steps  Finalizing the sizing code  Including the new technologies into the sizing  Constructing a preliminary CAD geometry for the aircraft 27

28. References  Boeing http://www.boeing.com  Airbus http://www.airbus.com  NASA www.aeronautics.nasa.gov/isrp/era/index.htm  MIT http://aviationweek.typepad.com/files/mit_n3_final_presentation.pdf  Northrop Grumman http://aviationweek.typepad.com/files/northrop_grumman_final.pdf  Aviation Week http://www.aviationweek.com/aw/commercial/  Perforated Fairings for Landing Gear Noise Control, N. Molin http://eprints.soton.ac.uk/43011/1/paper_vancouver_noabsolute_small.pdf 28