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Ovrhyp, Scramjet Test Aircraft STATE UNIVERSITY Student Authors: J https://ntrs.nasa.gov/search.jsp?R=19910000728 2020-03-19T20:21:21+00:00Z /z7 H OVRhyp, Scramjet Test Aircraft STATE UNIVERSITY Student Authors: J. Asian, T. Bisard, S. Dallinga, K. Draper, G. Hufford, W. Peters, and J. Rogers Supervisor: Dr. G. M. Gregorek Assistant: R. L. Reuss Department of Aeronautical & Astronautical Engineering Universities Space Research Association Houston, Texas 77058 Subcontract Dated November 17, 1989 Final Report May 1990 03/0_ OVRhyp, Scramjet Test Aircraft UNIVERSITY Student Authors: J. Asian, T. Bisard, S. Dallinga, K. Draper, G. Hufford, W. Peters, and J. Rogers Supervisor: Dr. G. M. Gregorek Assistant: R. L. Reuss Department of Aeronautical & Astronautical Engineering Universities Space Research Association Houston, Texas 77058 Subcontract Dated November 17, 1989 Final Report RF Project 767919/722941 May 1990 ABSTRACT (Gary Huff0rd} A preliminary design for an unmanned hypersonic research vehicle to test scramjet engines is presented. The aircraft will be launched from a carrier aircraft at an altitude of 4Q,0QQ feet at Mach 0.8. The vehicle will then accelerate to Mach 6 at an altitude of 100,000 feet. At this stage the prototype scramjet will be employed to accelerate the vehicle to Mach 10 and maintain Mach IQ flight for 2 minutes. The aircraft will then decelerate and safely land, presumably at NASA Dryden F[i_ht Test Center. ii TABLE OF CONTENTS ABSTRACT ............................ ii TABLE OF CONTENTS ....................... iii LIST OF FIGURES ......................... v INTRODUCTION .......................... vi CONFIGURATION .......................... WEIGHTS ANALYSIS ........................ 12 PURPOSE ............................. 12 METHOD ........................... 12 SYSTEMS .......................... 14 AERODYNAMIC SURFACES .................... 14 BODY STRUCTURE ....................... 15 THERMAL PROTECTION SYSTEM ................. 15 LAUNCH AND LANDING SYSTEM ................. 16 PROPULSION SYSTEM ..................... 16 INLET SYSTEM ........................ 16 CRYOGENIC FUEL SYSTEMS ................... 16 CONTROLS AND AVIONICS ................... 17 PROGRAM ......................... 17 CENTER OF GRAVITY TRAVEL CALCULATIONS ........... 17 AERODYNAMICS .......................... 19 INTRODUCTION ........................ 19 SUBSONIC .......................... 20 SUPERSONIC ............ , ............ 21 HYPERSONIC .......................... 22 PROGRAM USE ........................ 23 LONGITUDINAL STABILITY ..................... 29 SONIC BOOM ........................... 32 PROPULSION ........................... 34 Introduction ....................... 34 Rocket ........................... 35 Design ........................ 37 Rocket Design Calculations .............. 37 Rocket Spreadsheet Design ............... 38 TurbofanRamjet ...................... 39 Data ......................... 4e Scramjet .......................... 42 Profile ................. " ......... 46 Fue| Percentages ...................... 46 iii GLIDE CALCULATION ........................ 52 FLIGHT PLAN .......................... 54 SCRAMJET INLET DESIGN ...................... 56 TURBOFANRAMJET INLET ...................... 6O COOLING ............................. 66 Introduction ........................ 66 Cooling Methods .................... 66 Configuration ....................... 70 SUPPORT SYSTEMS ........................ 73 Control .......................... 73 Communication ....................... 74 COST ANALYSIS .......................... 76 CONCLUSION ........................... 78 FINAL NOTE .......................... 79 REFERENCES .......................... 8@ APPENDICES ........................... 82 Appendix A ......................... 83 Appendix B ......................... 92 Appendix C.1 ........................ 99 Appendix C.2 ...................... 105 Appendix C.3 ................... • .... 110 Appendix D ....................... 114 iv LIST OF FIGURES Figure I.I ........................ 6 Figure 1.2 ......................... 6 Figure 1.3: Final Configuration ................. 8 Figure 3.1: Current Configuration ............... 23 Figure 3.2:Reference Areas .................. 24 Figure 5.1: Surface Boom Pressure ................ 33 Figure 6.2: Rocket Equations ................. 38 Figure 6.3: Rocket Calculations ................. 39 Figure 6.4: Raw Data (Thrust/Drag) ............... 41 Figure 6.5: Fuel Flow Rate .................. 4t Figure 6.6: Raw Scramjet Thrust Data .............. 44 Figure 6.7: Scramjet Fuel Flow Rates .............. 43 Figure 6.8: Turbofan/Ramjet Spreadsheet ............ 44 Figure 6.9: Altitude vs. Mach No ................. 45 Figure 6.1@: Rocketed Fuel % ................... 47 Figure 6.11: Rocketless Fuel % .................. 47 Figure 6.12: Rocketed F Vs. M .................. 48 Figure 6.13: Rocketless F vs. M ................ 48 Figure 6.14: Rocketed Acc vs. M ................. 48 Figure 6.15: Rocketless Acc. vs. M ............... 48 Figure 6.17: Rocketed M vs. t ................. 49 Figure 6.18: Rocketless M vs. t ................. 49 Figure 6.19: Aft. vs. Dist .................... 5e Figure 6.2@: Alt. vs. t .................... 5O Figure 6.21: Dist. vs. t .................. 58 Figure 6.16: FFR vs. M ..................... 5O Figure 8.1: Flight Plan ................... 55 Figure [email protected]: Turbofan/Ramjet Inlet ............ 61 Figure [email protected]: External Ramps ................. 62 Figure [email protected]: Internal Ramps .................. 63 Figure [email protected]: Inlet Changes ................... 63 Figure [email protected]: Turbofan/Ramjet Inlet 3-view ............ 64 Figure [email protected]: Pressure Recovery ................. 65 Figure II.I: Transpiration cooling ............. 67 Figure 11.2: Direct cooling ................. 69 Figure II.3: Indirect cooling ................. 7O Figure 12.1: Control Diagram .................. 75 Figure 13.1: Cost Analysis ................... 76 Figure A.I: Initial configuration .............. 83 Figure A.2: Configuration 2 .................. 84 Figure A.3: Configuration 3 .................. 85 Figure A.4: Configuration 4 ................... 86 Figure A.5: Configuration 5 ................... 87 Figure A.6: Engine location .................. 88 F[_ure A.7: Reference values ................. 89 Figure A.8: Cut-away view .................... 9O Figure A.9: Final configuration ................. 9l V I NTRODUCT I ON (Gary Huff0rd) This report presents a preliminary design for a research vehicle to test scramjet engines. The goal of this vehicle is to test scramjet engines in a Mach 6 to Maeh 10 speed range. The purpose of this airplane is to use the vehicle to test scramjet engine technology. Since scramjets have not been flight tested, there reliability at present is questionable. Many flight tests will be necessary in the development of scramjet engines. A Mach 6 test must be successful before higher Mach number tests can be conducted since no other engine has an operating range above Mach 6. Thus, a vehicle design must be constructed that will allow many different Maeh number tests with a high degree of efficiency. The goal of this design of the research vehicle is to minimize the size and weight of the vehicle while still allowing the seramjets to be tested in the Maeh 6 to Mach 18 speed range. The vehicle is to be launched from a carrier aircraft at Mach 0.8 at 40,@@@ feet. By minimizing the size of the research vehicle, the size of the carrier aircraft can be minimized. A small vehicle (under 45@@@ pounds) may even have the capability to be launched from an existing airplane such as a B-52. Thus, a small vehicle may greatly reduce the cost of a scramjet engine flight test by reducing materia[ costs and by possibly eliminating the need to build a new carrier aircraft. The base design of the research vehicle is given in Figure i. Assuming the engine data given for the turbofanramjet and the scramjet vi is accurate, this vehicle has a maximum Mach number of 9.35. A two minute cruise can be conducted at any Mach number less than or equal to Mach 8.75. This design will allow initial scramjet tests to be conducted. Once the scramjets have been proven effective at Mach 8.75, rocket attachments can be made to the base design of Figure 1.2. These attach- ments are shown in Figure 1.3. The purpose of the rocket attachments is to increase the thrust in the transonic flight regime. An increase in thrust will eliminate the thrust pinch normally associated with this flight regime. A large increase in acceleration will reduce the fuel used by the turbofanramjet during transonic flight and will allow more fuel to be used by the scramjets at higher Mach numbers. The rocket attachments will increase the aerodynamic drag and the weight of the base design of the research vehicle. Thus, it is advantageous to eject the rockets after their fuel has been exhausted. Therefore, the drag and weight increases will be limited to the region where the rockets are in operation. Thus, the thrust gain will far outweigh the drag and weight penalty during the rockets region of operation. After the rocket fuel has been exhausted and the rockets ejected, the drag and weight of the vehicle will be the same as the base design of the research vehicle. The maximum Mach number of the design with rocket attachment is 9.9. The maximum Mach number for a two minute cruise is 9.25. Thus, the upper speed range for a scramjet test is increased by Mach .5 for the same vehicle design. Mach 9.9 is the maximum value the scramjet may be tested for any period of time for this vehicle. vii To obtain higher Mach number tests another scramjet
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