Systems Design Review

1. Systems Design • Review • N.E.R.D. • New Environmentally Responsible Design Dean Jones Dustin Souza Anthony Malito Ricardo Mosqueda Alex Fickes Keyur Patel Matt Dienhart Danielle Woehrle NayanapriyaBohidar

2. Outline • Mission Statement • Design Requirements • Aircraft Concept Selection • Advanced Technologies / Concepts • Engine / Propulsion Modeling • Constraint Analysis / Constraint Diagram • Sizing Studies • Initial Center of Gravity, Stability and Control Estimates • Summary of Aircraft Concepts

3. Mission Statement To design an environmentally responsible aircraft for the twin aisle commercial transport market with a capacity of 400 passengers, NASA’s N+2 capabilities, and an entry date of 2020-2025. NASA’s N+2 technology benefits include: • Reducing cumulative noise by 42 dB below Stage 4 • Reducing take-off and landing NOx emissions to 75% below CAEP6 levels • Reducing fuel burn by 50% • relative to “large twin-aisle performance” (777-200LR) • Reducing field length by 50% relative to the large twin-aisle

4. Design Requirements • Requirements • Threshold

5. Aircraft Concept Selection

6. Aircraft Concept Selection • Pros • Increased aerodynamic efficiency for lower drag • Decreased noise with engines mounted on top • Lighter structure • Cons • Increased manufacturing complexity • Increased maintenance costs The “Pocket Protectors” (2 Variations UDF or GTF)

7. Aircraft Concept Selection The “Side Part” • Pros • Conventional design • Decrease manufacturing cost • Decrease maintenance cost • Increase noise shielding • Cons • Not as efficient as a Blended Wing Body design

8. Aircraft Concept Selection The “Suspenders” • Pros • Semi-blended wing design • Circular pressure vessels • Maintenance and manufacturing complexity not as high as a BWB design • Cons • Higher drag from increased surface area

9. Cabin Layouts The “Suspenders” The “Side Part” The “Pocket Protectors”

10. Advanced Technologies

11. Engine Concepts Un-Ducted Fan (UDF) • Offering minimal fuel consumption • Double digit SFC • 30% Reduction in fuel consumption and greenhouse gases • Offering speed and performance of a turbofan • Bigger in size, noisy, safety issues Geared Turbofan (GTF) • 12% reduction in fuel consumption • 35-50% reduction in CO2 and NOx • 50% reduction in noise • Bigger in size • Fuel consumption is an issue

12. Rubber Engine Sizing

13. Constraint Analysis Pocket Protector Constraint assumptions L/D = 23.9 CL max = 2.16 CD0 = 0.0075 e = 0.9 AR = 12 αcruise = 0.322 αloiter= 0.739 Vcruise = 0.8 M VTO = 256.9 ft/s Vapproach = 283.1 ft/s

14. Constraint Analysis Pocket Protector Normal Operating Conditions High Hot Operating Conditions : H = 14K + 15°

15. Constraint Analysis Side Part Constraint assumptions L/D = 19.7 CL max = 1.8 CD0 = 0.015 e = 0.8 AR = 9 αcruise = 0.322 αloiter= 0.838 Vcruise = 0.8 M VTO = 240.6 ft/s Vapproach = 265.05 ft/s

16. Constraint Analysis Side Part - Normal Operating Conditions High Hot Operating Conditions- H = 14K +15°

17. Constraint Analysis Suspenders Constraint assumptions L/D = 21.8 CL max = 2.45 CD0 = 0.0138 e = 0.75 AR = 10.5 αcruise = 0.323 αloiter= 0.739 Vcruise = 0.8 Mach VTO = 260.9 ft/s @ sea level Vapproach = 268.1 ft/s @ sea level

18. Constraint Analysis Suspenders - Normal Operating Conditions High Hot Operating Conditions- H = 14K +15°

19. Sizing Study • Simple to Initial • L/D calculations implement results from trade studies • Component weight build-up method included in code (Raymer, eqs.15.46 – 15.59) • Component build-up technique underway for drag prediction (Raymer, eq. 12.24) • Best current predictions

20. Sizing Study • Validation

21. Center of Gravity Estimates

22. Control Sizing Approach • Tailless Concepts • Aerodynamic Center Location • Wing Sweep Tradeoffs • Traditional Tail Concepts • Tail Area

23. Next Steps • Implementing New Technologies • Geometry Sizing • Component weight distribution • Drag build-up • Stability Analysis • Internal layout and subsystems • Noise prediction • Concept refinement