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Integrated inward turning inlets and nozzles for hypersonic air vehicles
Integrated inward turning inlets and nozzles for hypersonic air vehicles
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机译:高超声速飞行器的集成的向内转向进气口和喷嘴
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摘要
A hypersonic waverider aircraft is disclosed that includes a first engine (106) and an inlet including a throat (108). The inlet is configured to generate three-dimensional flow compression during hypersonic flight with a weak shock wave that begins at the leading edge surfaces of the inlet and coalesces ahead of the throat, and a weak shock wave that begins at the point of coalescence of the weak shock wave and extends to the throat. The inlet includes a v-shaped lip open to freestream airflow in one side of the inlet.
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