SAWE Report - Cal Poly San Luis Obispo

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30 n 2 3 4 5 6 7 r = 2,000 ft 25 r = 4,000 ft Turn Rate (deg/s) 20 15 10 5 Stall Limit Max. P s = 0 Mil. P s = 0 RFP Requirement 8 deg/s r = 6,000 ft r = 8,000 ft r = 10,000 ft q Limit 0 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 2 Mach Figure 11.6 - Maneuverability Diagram at 15,000 ft (4,572 m) and Maneuver Weight 77
11.4 Mission Requirements By completing the design mission, the requirements for a supercruise Mach number of 1.6 and mission radius of 1,750 nm (3,240 km) are met. To determine the fuel capacity required to perform the design mission, the mission was simulated by numerically integrating the fuel burn rates over the mission profile. The mission simulation also allowed certain aspects of the mission such as cruise altitudes to be optimized. Table 11.V lists the results of the mission simulation, Figure 11.7 shows a breakdown of fuel consumption by mission segment, and Table 11.VI lists the fuel consumption by mission segment. Reserve 4% Misc. 5% Accelerate & Climb 12% Cruise Back 18% Cruise Out 28% Dash Back 15% Dash Out 18% Figure 11.7 - Fuel Consumption over Mission Table 11.V - Mission Results Total fuel consumption 57,940 lb (26,280 kg) Mission radius 1,750 nm (3,240 km) Total distance traveled over mission 3,980 nm (7,370 km) Total mission duration 4 hr. 57 min. Takeoff weight 124,800 lb (56,610 kg) Empty weight 56,270 lb (25,520 kg) Fuel weight (total fuel onboard) 59,250 lb (26,880 kg) Maneuver weight 95,830 lb (43,470 kg) Landing weight 57,550 lb (26,100 kg) Average cruise lift to drag ratio 6.6 78
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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
Page 37 and 38: 5.3 Wing Thickness The effect of wi
Page 39 and 40: 5.4 Airfoil The NACA 65A-003 airfoi
Page 41 and 42: 1 Section Lift Coefficient 0.9 0.8
Page 43 and 44: 90 80 Wing Cross Sectional Area (ft
Page 45 and 46: 6 Propulsion In developing the prop
Page 47 and 48: Table 6.II - RFP Dimensions Compare
Page 49 and 50: 38 Figure 6.1 - VAATE Goals
Page 51 and 52: TSFC 3.0 2.8 2.6 2.4 2.2 2.0 1.8 1.
Page 53 and 54: Deflection Angle Analysis for Mach
Page 55 and 56: Figure 6.8 - Cost Association with
Page 57 and 58: The inlet has a boundary layer dive
Page 59 and 60: 7 Materials and Structure The overa
Page 61 and 62: Vertical Attachment Points Horizont
Page 63 and 64: 8 Landing Gear Landing Gear design
Page 65 and 66: steel. This means that more braking
Page 67 and 68: Table 9.II - Final Component Weight
Page 69 and 70: throughout the 5-hour mission. Usin
Page 71 and 72: 10 Stability and Control To initial
Page 73 and 74: difference in neutral point and cen
Page 75 and 76: 40 30 20 10 0 -10 -20 -30 -40 -50 2
Page 77 and 78: The Vendetta configuration utilizes
Page 79 and 80: -0.6 -0.4 UNSTABLE NEUTRAL -0.2 Lif
Page 81 and 82: Validation of an aircraft design su
Page 83 and 84: consumption. The main aspects of th
Page 85 and 86: In addition to the performance requ
Page 87: 70,000 Altitude (ft) 60,000 50,000
Page 91 and 92: Table 11.VIII - Landing Flight Prof
Page 93 and 94: 11.7 Alternate Missions In addition
Page 95 and 96: 12 Payload Weapon internal layout d
Page 97 and 98: 13 Cockpit Cockpit Design began wit
Page 99 and 100: that could be used in landing and t
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 and 108: 16 Cost Analysis The final and perh
Page 109 and 110: Appendix Threats Chart Common Surfa
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,
Page 117: 35. www.dfrc.nasa.gov/PAO/PAIS/HTML
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SAWE Report - Cal Poly San Luis Obispo

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