Numerical Simulation of the Ejector-Jet Flowfield Around Small Rocket Exhaust
説明
In order to get experimental data in subsonic Mach number flight region, two small hybrid rockets installed the ejector-jet were launched, and then the flight analysis was performed. Numerical simulations were conducted for clarification of the flowfields and prediction of the ejector-jet performance. The CFD results revealed the compound compressible flow phenomena involving oblique shock waves and the subsonic flows. The effects of the flight Mach numbers and the rocket pressures to the suction performances were also investigated.
収録刊行物
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- 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
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16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009-06-14
American Institute of Aeronautics and Astronautics (AIAA)
