An application of the compressibility correction developed by Lieblein and Stockman (1972) to the calculation of flow in axisymmetric inlets is described. The results with experimental data from wind tunnel model tests are compared. The configuration is a conventional subsonic inlet with a NACA series one external cowl shape and a two-to-one ellipse internal lip. It is shown that the compressibility correction gives a relatively good approximation to the internal compressible flow behavior, and thus should be useful in the design and analysis of engine nacelle inlets.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Application of compressibility correction to calculation of flow in inlets.


    Contributors:

    Conference:

    Application of compressibility correction to calculation of flow in inlets ; 1973


    Publication date :

    1973-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :





    Compressibility Correction for Internal Flow Solutions

    S. LlEBLEIN AND N. O. STOCKMAN | AIAA | 1972


    Compressibility correction for flow about wing surfaces

    DIETRICH, D. A. / KROMER, S. L. / STOCKMAN, N. O. | AIAA | 1984