Asgard Aviation (formerly team 2)

1. Logan Waddell Morgan Buchanan Erik Susemichel Aaron Foster Asgard Aviation(formerly team 2) Craig Wikert Adam Ata Li Tan Matt Haas

2. Outline • Mission Statement • Market and Customers • Market size • Customer Benefits / Needs • Competition • Concept of Operations • Representative City Pairs • Payload / Capacity • Design Mission • System Design Requirements • Design Requirements • Benchmarking • Technologies / Advanced Concepts • Initial Sizing

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

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

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

6. Market / Customers • Steady increase in RPK since 1977, ~ 5% annually *Boeing • 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 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

9. Runway Length *MIT

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 Wpayload = 61250 lbs Wcrew = 1470 lbs

11. Design Mission

12. Typical Operating Mission

13. Design Requirements Compliance Matrix

14. Design Requirements ERA N+2 Requirements NASA Subsonic Fixed Wing Project Goals: • Noise prediction/reduction technologies for airframe/propulsion systems • Emissions-reduction technologies (mainly NOx) • Alternative Fuel Usage • Improved vehicle performance from: • Lightweight, durable structures • High-lift aerodynamics • Higher bypass ratio engines

15. Benchmarking • Info on Boeing aircraft from boeing.com • Info on Airbus aircraft from airbus.com

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

17. Technologies/Advanced concepts • Winglets • Blended • Spiroid • Multi-Winglets

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

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

21. Hybrid Laminar Flow Control • 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

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: We/W0=A*W0C*Kvs • 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

24. Aircraft Database Published Information (from Jane’s All the Worlds Aircraft and Boeing.com) Boeing 767-200ER Airbus A330-200

25. Sizing Code Predictions Boeing 767-200ER Airbus A330-200 • The initial sizing calculations prove to be mostly accurate on both of the baseline aircraft

26. Our Design Predictions

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

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