Propulsion-induced aerodynamic effects are computed by using data obtained from tests of a full-scale model of the E-7A configuration that were run in the NASA Ames 40 x 80 and 80 x 120-foot tunnels. These effects are shown both in aerodynamic coefficients and nondimensionalized by thrust versus equivalent velocity. The test results show that the full-scale ventral nozzle-induced effects are smaller than scale model data, while the ejector-induced effects demonstrate fair agreement. The effect of tunnel test section size is primarily observed at low and static speed, high thrust conditions, as seen in comparisons of data from both tunnels. The 80 x 120-foot tunnel test gave better static thrust calibrations and permitted a greater range of test freestream velocities and angles-of-attack, extending the database provided by the full-scale model.


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    Title :

    Propulsion-induced aerodynamics of an ejector-configured STOVL fighter aircraft


    Contributors:

    Publication date :

    1991-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Propulsion-induced aerodynamics of an ejector-configured STOVL fighter aircraft

    POPPEN, WILLIAM / SMITH, BRIAN / LYE, J. | AIAA | 1991




    Supersonic STOVL ejector aircraft from a propulsion point of view

    Luidens, R. W. / Plencner, R. / Haller, W. et al. | NTRS | 1984


    Supersonic STOVL ejector aircraft from a propulsion point of view

    LUIDENS, R. / PLENCNER, R. / HALLER, W. et al. | AIAA | 1984