Vendetta Final Proposal Part 1 (3.4 MB) - Cal Poly

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9080WingCross Sectional Area (ft 2 )706050403020Sears-HaackFuselageVertical TailHorizontal Tail1000 200 400 600 800 1,000Fuselage Station (inches aft datum)Figure 5.11 - Supersonic Area Distribution (Mach 1.6)Table 5.II - Parasite Drag Component Buildup (50,000 ft, Mach 0.5)Component Wetted Area Length Re F F Q F C f C DFuselage 2,500 ft 2 100.0 ft 59,060,935 1.09 1.10 0.00224 0.00446Wing 1,714 ft 2 32.0 ft 18,878,786 1.22 1.00 0.00266 0.00370Horizontal Tail 528 ft 2 15.0 ft 8,859,140 1.22 1.08 0.00299 0.00139Vertical Tail 330 ft 2 10.7 ft 6,319,520 1.22 1.08 0.00316 0.00092Σ 0.010470.060.05Drag Coefficient0.040.030.02300.02Induced DragTrim Drag0.01Wave DragParasite Drag00 0.5 1 1.51.62 2.5 3MachFigure 5.12 - Drag Build-Up at 50,000 ft, Maneuver Weight, and 5% Static Margin25
6 PropulsionIn developing the propulsion system for the <strong>Vendetta</strong>, the RFP specifications of supersonic cruise and stealth arethe driving factors. Due to the frontal RCS requirement, the fan blades of the engine must remain hidden which drivesthe engine placement well inside the aircraft.6.1 Engine SelectionThe RFP specifies a Low-Bypass-Ratio Turbofan (LBR-TF) or a Turbojet (TJ) engine may be used to perform themission. Both sizing equations and a candidate engine deck, an axisymmetric center body inlet and a mixed flow ejectornozzle, were supplied with the RFP, with an option to use either or neither. Since it included physical dimensions andfuel flow values the RFP engine deck was used instead of the equations provided by the RFP. The RFP enginespecifications are shown in Table 6.I.Table 6.I - Engine Specifications of RFP Supplied EngineEngine and Nozzle LengthPropulsion System LengthFan Face DiameterMaximum DiameterWeight with Nozzle310 in425 in50 in65 in7200 lbThe engine supplied by the RFP includes fuel flow and thrust data for part power, idle power, and military power.All engine data supplied by the RFP are corrected to sea level and a Mach number of zero. Therefore, every value forthrust and fuel flow at each altitude and Mach number is given in corrected net propulsive force (NPF c ) and correctedfuel flow (W Fc ). To find the actual thrust (NPF) and fuel flow (W F ) the following equations were used:NPF = NPF ⋅ dcT0.6F=F⋅c T⋅TW W Q ddT= +MPP2 3.5(1 .2 ) ( )SLT2QT= 1+0.2 M ( ) TSLOnce the data were uncorrected the military thrust was found. The RFP supplied equations that could be used to scale theengine based on a desired thrust. The scaling equations are as follows:26
Page 6 and 7: Figure 11.1 - 1-g Military Specific
Page 8 and 9: Nomenclature6DOF Six Degrees of Fre
Page 10: 1 IntroductionThe American Institut
Page 13 and 14: Table 1.III - Comparison of the F-1
Page 15 and 16: The weight fraction method provides
Page 17 and 18: 3 ConfigurationThe current configur
Page 19 and 20: • Span = 53 ft• m.a.c. = 32 ft
Page 21 and 22: VendettaChris DroneyNate SchnaibleK
Page 23 and 24: low signature axisymmetric advanced
Page 25 and 26: 0° Lookup77°50403020100-10-20-30-
Page 27 and 28: 5.2 Wing SweepThe next wing paramet
Page 29 and 30: 5.3 Wing ThicknessThe effect of win
Page 31 and 32: 0.10.050-0.05-0.1-0.150 0.1 0.2 0.3
Page 33: 5.6 DragDrag was divided into four
Page 37 and 38: Turbine Engine Technology (IHPTET)
Page 39 and 40: 35,00030,000Sea Level 1.5K 5K10K20K
Page 41 and 42: 0.990.980.97Pressure Recovery0.960.
Page 43 and 44: oundary layer diverter for high spe
Page 45 and 46: 7 Structural Layout & Material Sele
Page 47 and 48: Vertical AttachmentPointsHorizontal
Page 49: 8 Landing GearLanding Gear design f

Vendetta Final Proposal Part 1 (3.4 MB) - Cal Poly

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