Integrated inward turning inlets and nozzles for hypersonic air vehicles

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.