1. PROPRIETARY James Bearman AJ Brinker Dean Bryson Brian Gershkoff Kuo Guo Joseph Henrich Aaron Smith Daedalus Aviation Conceptual Design Review: “The Daedalus One”

2. PROPRIETARY April 17, 20082  Current Configuration  Mission and Requirements  Advanced Technologies  Carpet Plots and Sizing  Design Trade-Offs  Structural Considerations  Aerodynamics  Performance  Cost  Logistics

3. PROPRIETARY April 17, 20083 Advanced Avionics Geared Turbofans Lifting Canard Supercritical Airfoil Upper Surface Blown Flaps Composite Structure

4. PROPRIETARY April 17, 20084

5. PROPRIETARY April 17, 20085 Daedalus One Mission  Provide a versatile aircraft with medium range and capacity to meet the needs of a commercial aircraft market still expanding in the year 2058  Incorporate the latest in technology to provide reliability, efficiency, while fulfilling the need for an environmentally friendly transportation system  Possess the ability to operate at nearly any airfield 5

6. PROPRIETARY April 17, 20086 Mission Profiles Mission One Schaumburg to North Las Vegas 1300 nmi Mission Two South Bend to Burbank 1580 nmi Mission Three West Lafayette to Urbana-Champaign to Cancun 1200 nmi Mission Four Minneapolis to LAX 1330 nmi 6

7. PROPRIETARY April 17, 20087

8. PROPRIETARY April 17, 20088  Composites  Stronger, lighter aircraft  Artificial Intelligence/Automated Pilot  Reduction in flight crew  Automatic flight control, collision avoidance  Fly by Light  Weight savings over copper wire  Faster response

9. PROPRIETARY April 17, 20089  Capability to increase C Lmax to 7  Wing C Lmax (clean) ≈ 1.54  Takeoff C L (w/ upper surface blowing) ≈ 4 --Nicolai, Fundamentals of Aircraft Design, 1976

10. PROPRIETARY April 17, 200810 http://www.flug-revue.rotor.com/FRHeft/FRHeft07/FRH0702/FR0702c1.JPG  The Geared Turbofan  Current predictions say: “The Geared Turbofan engine will deliver a 12 percent reduction in fuel burn, 50 percent reduction in noise and emissions, and 40 percent reduction in maintenance costs over today's commercial engines.” –www.pw.utc.com  By 2038 we believe it will achieve over current technology: ▪ 30% reduction in fuel burn ▪ 75% reduction in noise and emissions ▪ 50% reduction in maintenance costs

11. PROPRIETARY April 17, 200811 http://www.flug-revue.rotor.com/FRHeft/FRHeft07/FRH0702/FR0702c1.JPG  Thrust per engine - 25,000 lbs  SFC per engine - 0.42/hour  Fan Diameter - 8 ft.  Bypass Ratio - 8

12. PROPRIETARY April 17, 200812  Geared Turbofans reduce CO2 produced by more than 12% compared to today’s engines  Reduce cumulative noise levels about 20dB below the current Stage 4 regulations

13. PROPRIETARY April 17, 200813  Low wing with Geared Turbofans mounted at the leading edge  Easy location for engine maintenance ▪ Geared Turbofan engines reduce maintenance costs by 40% over today's commercial engine  No complicated powered lift devices

14. PROPRIETARY April 17, 200814  Generation  Takeoff weight generated through RDS  Initial starting point ▪ T/W=.23 ▪ W/S=84  Carpet Plot Range ▪ T/W=0.23 - 0.414 ▪ W/S=84 - 160  Varied Wing Sweep (and saved 5,000 lbs)

15. PROPRIETARY April 17, 200815  Constraints Used  Fuel Burn per Seat-Mile  Field Length with OEI  Cruise Speed 0.75M  Constraints Not Used  Takeoff Ground Roll  Field Length All Engines Operational  Landing Ground Roll

16. PROPRIETARY April 17, 200816

17. PROPRIETARY April 17, 200817  Carpet Plots  Approximated Design Point  RDS  Primary Method of Sizing  MATLAB Code for Component Weight Breakdown

18. PROPRIETARY April 17, 200818 Taxi Takeoff & Climb Step Cruise For Best Range Descend & Hold Land & Taxi Climb- Miss Approach Cruise Descend & Hold Land & Taxi  Maximum Range Mission (1,800 nmi)  Typical Commercial Mission Profile  Maximizes Aircraft Range  Fuel Reserves (200 nmi)  Extended Loiter Time  Flight Diversion to Another Airport

19. PROPRIETARY April 17, 200819  Input Parameters  W/S – 120  T/W – 0.32  AR – 14  Λ wing – 10°  λ wing – 0.4  (C L ) TO – 4  Weights  GTOW – 87,100 lbs  W e – 34,700 lbs  W f – 24,600 lbs  Payload – 27,800 lbs  W e / W o – 0.40  W f / W o – 0.28

20. PROPRIETARY April 17, 200820  Structures ~ 20,000 lbs  Wing ~ 8,300 lbs  Fuselage ~ 7,200 lbs  Canard ~ 600 lbs  Vert. Tail ~ 600 lbs  Landing Gear ~ 3,300 lbs  Propulsion ~ 8,100 lbs  Engines ~ 7,000 lbs  Fuel System ~ 900 lbs  Systems ~ 200 lbs  Equipment ~ 7,000 lbs  Controls ~ 2,800 lbs  Avionics ~ 2,100 lbs

21. PROPRIETARY April 17, 200821 Daedalus One

22. PROPRIETARY April 17, 200822

23. PROPRIETARY April 17, 200823  108 Seats, Single Class  Seat Pitch: 32 in  Seat Width: 20 in  Aisle Width: 24 in  2 Galley Areas: 35 and 16 ft 2  2 Lavs: ~20 ft 2

24. PROPRIETARY April 17, 200824  Initial design: High Wing Low Canard  Current Design: Low Wing High Canard ▪ Reason: Landing gear placement, better accessibility for ground service, easier to maintain with lower wing  Wing Sweep Study: Result 10°  Varied Sizing Based on 10° sweep and 20° sweep ▪ Reason: Find the most weight efficient aircraft  Upper Surface Blowing  Placed engines above the wings near leading edge ▪ Reason: Increase lift especially for takeoff and landing

25. PROPRIETARY April 17, 200825  Initial Design: Tri-tail  Current Design: Single Tail ▪ Reason: Reduced weight, sizing proved 3 Tails not needed  Forward Wing Extension ▪ Reason: Allows more fuel, helps move Center of Gravity forward  Elliptical Fuselage ▪ Reason: Allow for more comfortable passenger cabin

26. PROPRIETARY April 17, 200826

27. PROPRIETARY April 17, 200827

28. PROPRIETARY April 17, 200828

29. PROPRIETARY April 17, 200829  Main Wing-Super Critical 20712  Representative (custom airfoil to be developed)  Data obtained from analysis in Fluent  12% thick airfoil  Allows for high cruise speed via controlling shock formation

30. PROPRIETARY April 17, 200830  Zero lift angle of attack ≈ -5°  Max C l ≈ 1.7  Stall Angle ≈ 18°

31. PROPRIETARY April 17, 200831  Canard and Tail-Super Critical 20012  Data obtained from analysis in Fluent  Symmetric airfoils are standard for vertical and horizontal tails

32. PROPRIETARY April 17, 200832  Zero Lift Angle of Attack ≈ 0 °  Max Cl ≈ 1.18  Stall Angle ≈ 15°

33. PROPRIETARY April 17, 200833 Stall Limit Absolute Ceiling Service Ceiling q Limit

34. PROPRIETARY April 17, 200834

35. PROPRIETARY April 17, 200835 GTOW W 0f + reserves OWE + payload OWE WeWe W e + trapped fuel

36. PROPRIETARY April 17, 200836  Canard  S canard : 300 ft 2  Elevator Area Ratio: 1/3  AR: 4  Sweep: 15°  Taper Ratio: 0.4

37. PROPRIETARY April 17, 200837  Vertical Tail  Sized for One Engine Out at Takeoff  S tail : 310 ft 2  Rudder Area Ratio: 1/3  AR: 2  Sweep: 15°  Taper Ratio: 0.4

38. PROPRIETARY April 17, 200838  RDT&E Cost: $24.4B USD (2008)  Cost per aircraft: $49M USD  Sale Price: $54M USD  Break Even Point: 455 Aircraft  Operating Cost: $11.5M USD/Yr  $0.0616/seat-mile USD  Jet A: $2.50/Gal

39. PROPRIETARY April 17, 200839 Jetway Tow Baggage Fuel Water Baggage Galley Electric Lav

40. PROPRIETARY  108 Passenger Capacity  1800 nmi Range  2700 ft Takeoff Ground Roll  Affordable Acquisition Cost  Reasonable Operational Cost  Opens new markets  Enhances service to existing markets  Improves reliability and ease of air travel  Allows air travel industry to expand beyond current limits April 17, 200840

41. PROPRIETARY

42. April 17, 200842

43. PROPRIETARY April 17, 200843

44. PROPRIETARY April 17, 200844