As flight speeds increase, supersonic aircraft powerplant installations may encounter complex aerodynamic problems due to shock reflection and possibility of inlet shock instability created by pod-to-pod interference; experimental program conducted at United Aircraft Corp and wind tunnel test data obtained during study of adjacent inlet interference are presented; program established, for Mach 3.0 design mixed compression inlet, dividing line between regions of expelled shock interference and completely stable operation; study was also conducted to determine effect of placing plate between pods.


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    Title :

    Inlet-to-inlet shock interference tests


    Additional title:

    NASA CR


    Contributors:

    Published in:

    Publication date :

    1965


    Size :

    45 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English




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