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SAWE Paper No. 3232 Category No. 10
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Table of Contents Abstract_________
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List of Figures Figure 1.1 - Design
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Figure 13.4 - Rectilinear Vision Pl
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Nomenclature AIAA American Institut
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α Angle of Attack, degrees, rad.
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Table 1.II - Summary of Design Requ
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Figure 1.3 - F-15 Strike Eagle F-11
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Table 1.III - Comparison of the F-1
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Many of the equations buried in the
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3 Configuration The current configu
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Another problem arises from the 20
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• Span = 54.7 ft • m.a.c. = 32
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4 Stealth Considerations As mention
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Table 4.I - Common Ground Radars Ra
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30 20 10 0 -10 -20 -30 -40 -50 1 GH
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5 Aerodynamics The major aerodynami
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1 GHz. 40º LE Sweep 10 GHz. 40º L
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5.3 Wing Thickness The effect of wi
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5.4 Airfoil The NACA 65A-003 airfoi
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1 Section Lift Coefficient 0.9 0.8
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90 80 Wing Cross Sectional Area (ft
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6 Propulsion In developing the prop
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Table 6.II - RFP Dimensions Compare
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38 Figure 6.1 - VAATE Goals
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TSFC 3.0 2.8 2.6 2.4 2.2 2.0 1.8 1.
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Deflection Angle Analysis for Mach
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Figure 6.8 - Cost Association with
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- Page 59 and 60: 7 Materials and Structure The overa
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- Page 63 and 64: 8 Landing Gear Landing Gear design
- Page 65 and 66: steel. This means that more braking
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- Page 69 and 70: throughout the 5-hour mission. Usin
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- Page 73 and 74: difference in neutral point and cen
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- Page 77 and 78: The Vendetta configuration utilizes
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- Page 83 and 84: consumption. The main aspects of th
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- Page 89 and 90: 11.4 Mission Requirements By comple
- Page 91 and 92: Table 11.VIII - Landing Flight Prof
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- Page 101 and 102: 14 Systems The systems of the Vende
- Page 103 and 104: 14.3 Fuel System Initial fuel syste
- Page 105 and 106: 15 Manufacturing Several manufactur
- Page 107: 16 Cost Analysis The final and perh
- Page 111 and 112: Wing Break Point Fuel Aft Fuselage
- Page 113 and 114: The Vendetta Design Team Chris Atki
- Page 115 and 116: References 1. “Ejection Systems,
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