SAWE Report - Cal Poly San Luis Obispo

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S VT Vertical Tail Planform Area S w Wing Reference Area, ft 2 S wet Wetted Area, ft 2 T Thrust, lb T Temperature, R T/W Thrust to Weight Ratio T available Available Thrust, lb TOGW Takeoff Gross Weight, lb T required Required Thrust, lb TSFC Thrust Specific Fuel Consumption, lb/lb hr, lb/lb s V Velocity, knots, ft/sec V H Horizontal Tail Volume Coefficient V stall Stall Velocity, knots, ft/s V TD Touchdown Velocity, knots, ft/s V TO Takeoff Velocity, knots, ft/s V V Vertical Tail Volume Coefficient W Weight, lb W Fuel Flow Rate, slugs/s F W/S Wing Loading, lb/ft 2 a Speed of Sound, ft/s a Temperature Lapse Rate in Troposphere, R/ft c Chord c Mean Aerodynamic Chord, ft c Mean Aerodynamic Chord, ft w c root Root Chord, ft c tip Tip Chord, ft e Span Efficiency Factor f Component Fineness Ratio g Acceleration Due to Gravity, ft/s 2 h Altitude, ft k Surface Roughness, ft k 1 Induced Drag Coefficient l Length of Drag Component, ft n Load Factor ⎛ g ⎞ n Atmospheric Constant, ⎜n = = 5.2561⎟ ⎝ aR ⎠ q Dynamic Pressure, lb/ft 2 s Distance, n miles, ft t Time, s t Thickness of Wing to Chord Ratio y mac y Location of Mean Aerodynamic Chord, ft Λ LE Leading Edge Sweep, degrees, rad. Λ t max Sweep of Position of Maximim Thickness, degrees, rad. Trailing Edge Sweep, degrees, rad. Λ TE ix
α Angle of Attack, degrees, rad. α eff Effective Angle of Attack, degrees, rad. α i Angle of Attack Induced by Downwash, degrees, rad. δ T Engine Correction Factor γ Specific Heat Ratio γ Climb Angle, degrees, rad. λ Taper Ratio µ Dynamic Viscosity, lb s/ft 2 µ brake Braking Coefficient of Friction µ roll Rolling Coefficient of Friction θ T Engine Correction Factor ρ Density, slugs/ft 3 ψ Yaw Angle, degrees, rad. Subscripts 0 Sea-Level Value ∗ Value at Tropopause x
Page 1 and 2: SAWE Paper No. 3232 Category No. 10
Page 3 and 4: Table of Contents Abstract_________
Page 5 and 6: List of Figures Figure 1.1 - Design
Page 7 and 8: Figure 13.4 - Rectilinear Vision Pl
Page 9: Nomenclature AIAA American Institut
Page 13 and 14: Table 1.II - Summary of Design Requ
Page 15 and 16: Figure 1.3 - F-15 Strike Eagle F-11
Page 17 and 18: Table 1.III - Comparison of the F-1
Page 19 and 20: Many of the equations buried in the
Page 21 and 22: 3 Configuration The current configu
Page 23 and 24: Another problem arises from the 20
Page 25 and 26: • Span = 54.7 ft • m.a.c. = 32
Page 27 and 28: 4 Stealth Considerations As mention
Page 29 and 30: Table 4.I - Common Ground Radars Ra
Page 31 and 32: 30 20 10 0 -10 -20 -30 -40 -50 1 GH
Page 33 and 34: 5 Aerodynamics The major aerodynami
Page 35 and 36: 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 and 88:
70,000 Altitude (ft) 60,000 50,000
Page 89 and 90:
11.4 Mission Requirements By comple
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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