Proposed configurations for the next generation of transatmospheric vehicles will rely on air breathing propulsion systems during all or part of their mission. At flight Mach numbers greater than about 7 these engines will operate in the supersonic combustion ramjet mode (scramjet). Ground testing of these engine concepts above Mach 8 requires high pressure, high enthalpy facilities such as shock tunnels and expansion tubes. These impulse, or short duration facilities have test times on the order of a millisecond, requiring high speed instrumentation and data systems. One such facility ideally suited for scramjet testing is the NASA-Ames 16-Inch shock tunnel, which over the last two years has completed a series of tests for the NASP (National Aero-Space Plane) program at simulated flight Mach numbers ranging from 12-16. The focus of the experimental programs consisted of a series of classified tests involving a near-full scale hydrogen fueled scramjet combustor model in the semi-free jet method of engine testing whereby the compressed forebody flow ahead of the cowl inlet is reproduced (see appendix A). The AIMHYE-1 (Ames Integrated Modular Hypersonic Engine) test entry for the NASP program was completed in April 1993, while AIMHYE-2 was completed in May 1994. The test entries were regarded as successful, resulting in some of the first data of its kind on the performance of a near full scale scramjet engine at Mach 12-16. The data was distributed to NASP team members for use in design system verification and development. Due to the classified nature of the hardware and data, the data reports resulting from this work are classified and have been published as part of the NASP literature. However, an unclassified AIAA paper resulted from the work and has been included as appendix A. It contains an overview of the test program and a description of some of the important issues.
Shock-Tunnel Combustor Testing for Hypersonic Vehicles
1994
33 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Jet & Gas Turbine Engines , Aerodynamics , Combustion chambers , Engine tests , Hypersonic aircraft , Hypersonic flow , Hypersonic inlets , Inlet nozzles , Propulsion system performance , Supersonic combustion ramjet engines , Wind tunnel tests , Air breathing engines , Hypersonic speed , Mach number , Propulsion system configurations , Two dimensional flow , Flow distribution , Hydrogen fuels , Hypersonic wind tunnels , Inlet flow , Inlet pressure , National aerospace plane program , Pressure distribution , Shock tunnels , Transatmospheric vehicles , Wind tunnel models
Shock-tunnel combustor testing for hypersonic vehicles
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Tema Archiv | 1995
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AIAA | 1993
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Online Contents | 1995
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British Library Conference Proceedings | 1992
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