Integrated inward turning inlets and nozzles for hypersonic air vehicles
    7.
    发明申请
    Integrated inward turning inlets and nozzles for hypersonic air vehicles 有权
    集成向内转向入口和喷嘴用于超音速飞行器

    公开(公告)号:US20070187550A1

    公开(公告)日:2007-08-16

    申请号:US11354358

    申请日:2006-02-14

    申请人: John Elvin

    发明人: John Elvin

    IPC分类号: B64C1/00

    摘要: A hypersonic waverider aircraft is disclosed that includes a first engine and an inlet including a throat. 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.

    摘要翻译: 公开了一种超音速摇摆飞机,其包括第一发动机和包括喉部的入口。 入口配置为在超音速飞行期间产生三维流动压缩,其中弱冲击波从入口的前缘表面开始并在喉部之前聚结,并且在聚结点处开始的弱冲击波 弱冲击波延伸到喉咙。 入口包括一个v形嘴,可以在入口一侧的自由流气流中开口。