Zero-length inlet performance and associated fan blade stresses were determined during model tests in the NASA-LeRC 9-by 15-foot low-speed wind tunnel. The inlet models, which were installed on a 20-inch diameter fan unit, had different inlet lip contraction ratios as well as unslotted, slotted, and double slotted inlet lips. The inlet angle-of-attack boundaries for onset of flow separation were identified and compared to the operating requirements of several generically different subsonic V/STOL aircraft. The zero-length inlets, especially those with slotted lips, were able to satisfy these requirements without compromising the maximum cowl forebody radius. As an aid to the inlet design process, a unique relationship was established between the maximum surface Mach number associated with the separation boundary and the maximum-to-throat surface velocity ratio.


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    Title :

    Zero-length inlets for subsonic V/STOL aircraft


    Contributors:

    Conference:

    Joint Propulsion Conference ; 1981 ; Colorado Springs, CO, US


    Publication date :

    1981-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Zero-length inlets for subsonic V/STOL aircraft

    GLASGOW, E. R. / BECK, W. E. / WOOLLETT, R. R. | AIAA | 1983


    Zero-length inlets for subsonic V/STOL aircraft

    GLASGOW, E. / BECK, W. / WOOLLETT, R. | AIAA | 1981


    Zero-length inlets for subsonic V/STOL aircraft

    Glasgow, E. R. / Beck, W. E. / Woollett, R. R. | NTRS | 1983