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Preliminary Design Review EcoJet

Preliminary Design Review EcoJet. Group 2. Mike Dumas Adam Naramore Ben Scott. Gaetano Settineri Tim Sparks David Wilson. Market. Target buyers are fractional ownership operators Market Capture Target (Next 5 Years) 2.5% Total Market 25 Aircraft Growth Estimates (5+ Years)

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Preliminary Design Review EcoJet

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  1. Preliminary Design ReviewEcoJet Group 2 Mike Dumas Adam Naramore Ben Scott Gaetano Settineri Tim Sparks David Wilson

  2. Market • Target buyers are fractional ownership operators • Market Capture Target (Next 5 Years) • 2.5% Total Market 25 Aircraft • Growth Estimates • (5+ Years) • 5% Total Market or 50 Aircraft • Growth Forecast (By 2022) • 7% Light-Medium Market or 260 Aircraft

  3. Design Requirements

  4. Design Mission

  5. 3-D Model

  6. 3-view 55ft 7 ft 13ft 50ft 100

  7. Cabin Layout Sleeper Seats Closet Seats Lavatory Cockpit Refreshment Center Door

  8. Sizing • GTOW: 26,144 lbs • W/S: 70 lb/ft2 • T/W: 0.45 lbf/lbm • AR: 8.3 • Wing sweep: 30 degrees • Taper Ratio: 0.32 • Dihedral: 10.3 degrees

  9. Compliance with Design Requirements

  10. Flops Sizing • Flops Analysis • Gross Takeoff Weight Max = 30,000 lbs • W/S = 65 - 75 lb/ft^2 • T/W = 0.4 - 0.5 (output of approx. 5751.7 lbf/engine) • Analysis done with Fixed Mach # and Altitude • Cruise Mach # = 0.85 • Cruise Alt.= 41,000 ft. • IFR range accounted for in flops • 100 nm. Alternate airport range • 45 min. Loiter

  11. Flops Sizing

  12. Drag Polars: From Flops Mach #

  13. Drag Polar Comparison Good Comparison between FLOPS Data and Raymer Code • Reasons for Error: • Inaccurate Raymer Wave Drag Approx. • No FLOPS airfoil input • Inaccurate Span Efficiency

  14. Flight Performance Envelope

  15. V-N Diagram Load factor (g’s) Stall Speed Velocity (ft/sec)

  16. Structural Layout • Wing box occupies 7-70% of the chord length • Wing box carries through the fuselage • Ribs are spaced 5 ft apart • Spar web thickness: 0.25 in • Forward wing spar flange thickness: 0.5 in • Aft wing flange thickness: 0.4in • Rib thickness: 0.2 in

  17. Materials • Wing/Fuselage Skin: AS4/3501-6 Graphite Epoxy • Quasi-isotropic lay-up: [±45/0/90]s2 • Ply thickness: 0.005 in • Wing Box/Ribs: Al 2017

  18. C. G. and Weight Estimates Utilized Equations from Raymer, Chapter 15 Weights from Cargo/Transport Category were Averaged with Weights from GA Category Location of the CoM for each Component was Estimated from 3-D Model Static Margin was Calculated as a Percent of the MAC Static Margin Limits were taken from Course Notes for Stanford University AAE241 (http://adg.stanford.edu/aa241/stability/staticstability.html)

  19. Weight Breakdown

  20. Propulsion • Fuel: B100 Bio-diesel • Estimated Max TO thrust: ~5300 lbs/engine • Overall Pres. Ratio = 20 • Fan Pres. Ratio = 2.9 • Bypass Ratio = 3.2 • Best SFC: 0.88 lbm/lbf/hr • Garret’s TFE731-60 engine

  21. Cost Analysis • Final Estimated DOC: $1,062/hr • Final Estimated Acquisition Cost: $14.5 mil • Developed from: • FLOPS • Historical data • Estimates of new technology and design factors

  22. Summary • Open issues: • Reduce GTOW • Fuel Testing • Acquisition Cost • Optimization of wing structure • CFD

  23. Questions?

  24. Extra Slides

  25. Airfoil Choice • Over 40 Airfoils Compared • Wings – NACA 64212 • Wing Elevator Section & Vertical Tail – NASA - SC20010

  26. Reynolds Number • Based on 41,000 ft at 480 kts Fuselage – 7.59 x 107 Fore Wing – 2.74 x 105 Aft Wing – 2.19 x 105

  27. Airfoil SC20010

  28. Airfoil NACA 64212

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