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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

Preliminary Design ReviewEcoJet

Group 2

Mike Dumas

Adam Naramore

Ben Scott

Gaetano Settineri

Tim Sparks

David Wilson

market
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 view
3-view

55ft

7 ft

13ft

50ft

100

cabin layout
Cabin Layout

Sleeper

Seats

Closet

Seats

Lavatory

Cockpit

Refreshment

Center

Door

sizing
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
flops sizing
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
drag polar comparison
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
v n diagram
V-N Diagram

Load factor (g’s)

Stall Speed

Velocity (ft/sec)

structural layout
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
materials
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
c g and weight estimates
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)

propulsion
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
cost analysis
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
summary
Summary
  • Open issues:
    • Reduce GTOW
    • Fuel Testing
    • Acquisition Cost
    • Optimization of wing structure
    • CFD
airfoil choice
Airfoil Choice
  • Over 40 Airfoils Compared
  • Wings – NACA 64212
  • Wing Elevator Section & Vertical Tail – NASA - SC20010
reynolds number
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