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

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Figure 6.1 - VAATE GoalsDepartment of Defense Office of the Deputy Under Secretary of Defense Mr. Paul F. PiscopoIt is likely that this program will face similar problems in achieving its goal by 2010, in which case a decrease of15% in TSFC was taken and an estimated 25% decrease in cost over the F119. The 15% change in TSFC was achievedby increasing the uninstalled thrust by 13% and decreasing the fuel flow 4%. The new VAATE technology engine has asea level uninstalled thrust of 30,000 lbs and an uninstalled cruise TSFC of 0.80 lbm/lbf-hr, however once inlet andducting losses are accounted for the cruise TSFC is 0.90 lbm/lbf-hr. The resulting uninstalled engine deck for <strong>Vendetta</strong> issupplied in Appendix A. The engine deck is correct to static sea level conditions similar to the engine deck provided bythe RFP.The uninstalled military thrust and TSFC of the engine at various altitudes can be seen in Figure 6.2 and Figure6.3, respectively. The afterburner model was created based on information given in a presentation on the LockheedMartin JSF test program. The approximate afterburner thrust was given as 40,000 lbs, and the dry thrust at 27,000 lbs.This resulted in a maximum thrust 1.5 times military. A maximum TSFC of 2 lbm/lbf-hr was used as most modernengines produce a value around 2 for maximum TSFC.29
35,00030,000Sea Level 1.5K 5K10K20K 25K 30K 36,089Thrust (lbF)25,00020,00015,00010,0005,00043K50K55K60K65K70K00 0.5 1 1.5 2 2.5 3Mach NumberFigure 6.2 - Thrust Curves for Altitudes from Sea Level to 70,000 ft1.2TSFC (1/hr)10.80.60.4Sea Level1.5K5K10K20K 25K 30K 70K65K60K55K50K43K360890.200 0.5 1 1.5 2 2.5 3Mach NumberFigure 6.3 - Military TSFC Curves for Altitudes from Sea Level to 70,000 ftOnce the engine deck had been generated the engine dimensions were once again considered. The fan facediameter of the new engine was assumed to be that of the current General Electric F136 engines that are being tested.They are currently using a fan face diameter of 48 inches (even though production engines will use a 43 inch diameterfan face). Low bypass turbofans typically have smaller fan face diameters; however, as the bypass ratio increases the fanface diameter would increase as well. Since future technology is being taken into account it is likely that the engine thatwould produce this thrust would have a larger bypass ratio but a smaller core keeping the fan face diameter comparableto current sizes. The length of the engine was estimated based on lengths of recent engines. Engines used for comparisoninclude the F100, F101, F110, and F404. Engine lengths varied from about 150 to 200 inches. The engine length wasdetermined to be 192 inches as this engine is a more advanced engine requiring higher thrust production.30
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 and 34: 5.6 DragDrag was divided into four
Page 35 and 36: 6 PropulsionIn developing the propu
Page 37: Turbine Engine Technology (IHPTET)
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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