SAWE Report - Cal Poly San Luis Obispo

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Abstract <strong>Cal</strong> <strong>Poly</strong> proudly presents the Vendetta, a supersonic bomber designed to meet the criterion specified by the AIAA 2001/2002 Undergraduate Team Aircraft Design Request for Proposal. The mission to be flown by the Vendetta consists of a 1,750 nautical mile radius, all of which must be flown at Mach 1.6 at or above 50,000 feet. The aircraft must have low frontal radar cross-section and also be capable of dropping a 9,000-pound weapons payload. The Vendetta is being designed to replace the stealthy F-117 Nighthawk and B-2 Spirit as well as the supersonic F-15 Eagle and B-1 Lancer. The Vendetta’s current takeoff gross weight is 125,000 pounds and its empty weight is 57,000 pounds. Furthermore, an analysis from a low observables standpoint has been made possible by publicly accessible RCS code. The component weight buildup of the Vendetta has been developed using both class I and class II methodologies as well as by assigning mass properties to an actual solid model of the aircraft. Several challenges concerning the balance of the aircraft have been introduced by the immediate and abrupt shift in the aerodynamic center due to the acceleration from subsonic to supersonic Mach numbers. Solutions to this problem have been developed and will be presented in the report. i
Table of Contents Abstract______________________________________________________________________ i Table of Contents _____________________________________________________________ ii List of Figures________________________________________________________________ iv List of Tables _______________________________________________________________ vii Nomenclature _______________________________________________________________viii 1 Introduction______________________________________________________________ 1 2 Defining the Design Domain ________________________________________________ 7 3 Configuration ___________________________________________________________ 10 4 Stealth Considerations ____________________________________________________ 16 5 Aerodynamics ___________________________________________________________ 22 5.1 Wing Sizing ________________________________________________________ 22 5.2 Wing Planform ______________________________________________________ 23 5.3 Wing Thickness _____________________________________________________ 26 5.4 Airfoil _____________________________________________________________ 28 5.5 Lift Curve __________________________________________________________ 28 5.6 Drag_______________________________________________________________ 31 6 Propulsion ______________________________________________________________ 34 6.1 Engine Selection _____________________________________________________ 34 6.2 Inlets ______________________________________________________________ 41 6.3 S-Duct _____________________________________________________________ 46 6.4 Nozzle _____________________________________________________________ 47 7 Materials and Structure____________________________________________________ 48 8 Landing Gear ___________________________________________________________ 52 9 Weight & Balance________________________________________________________ 55 10 Stability and Control____________________________________________________ 60 11 Performance __________________________________________________________ 71 11.1 Performance Requirements_____________________________________________ 71 11.2 Specific Excess Power Requirements_____________________________________ 74 11.3 Turn Rate Requirement________________________________________________ 76 11.4 Mission Requirements ________________________________________________ 78 11.5 Takeoff & Landing ___________________________________________________ 79 11.6 Performance Summary ________________________________________________ 81 11.7 Alternate Missions ___________________________________________________ 82 12 Payload ______________________________________________________________ 84 13 Cockpit ______________________________________________________________ 86 14 Systems ______________________________________________________________ 90 14.1 Auxiliary Power Generation System _____________________________________ 90 14.2 Vehicle Management System ___________________________________________ 91 14.3 Fuel System_________________________________________________________ 92 15 Manufacturing_________________________________________________________ 94 16 Cost Analysis _________________________________________________________ 96 Appendix___________________________________________________________________ 98 Threats Chart______________________________________________________________ 98 ii
Page 1: SAWE Paper No. 3232 Category No. 10
Page 5 and 6: List of Figures Figure 1.1 - Design
Page 7 and 8: Figure 13.4 - Rectilinear Vision Pl
Page 9 and 10: Nomenclature AIAA American Institut
Page 11 and 12: α Angle of Attack, degrees, rad.
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
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The inlet has a boundary layer dive
Page 59 and 60:
7 Materials and Structure The overa
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Vertical Attachment Points Horizont
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8 Landing Gear Landing Gear design
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steel. This means that more braking
Page 67 and 68:
Table 9.II - Final Component Weight
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throughout the 5-hour mission. Usin
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10 Stability and Control To initial
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difference in neutral point and cen
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40 30 20 10 0 -10 -20 -30 -40 -50 2
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The Vendetta configuration utilizes
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-0.6 -0.4 UNSTABLE NEUTRAL -0.2 Lif
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Validation of an aircraft design su
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consumption. The main aspects of th
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In addition to the performance requ
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70,000 Altitude (ft) 60,000 50,000
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11.4 Mission Requirements By comple
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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
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14 Systems The systems of the Vende
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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
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Appendix Threats Chart Common Surfa
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Wing Break Point Fuel Aft Fuselage
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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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