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    Supercritical airfoil drag reduction by passive shock wave/boundary layer control in the Mach number range .75 to .90

    Supercritical airfoil drag reduction by passive shock wave/boundary layer control in the Mach number range .75 to .90


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    Title :

    Supercritical airfoil drag reduction by passive shock wave/boundary layer control in the Mach number range .75 to .90

    Contributors:
    NAGAMATSU, H. (author) / FICARRA, R. (author)
    Conference:

    23rd Aerospace Sciences Meeting ; 1985 ; Reno , NV , U.S.A.

    Published in:

    23rd Aerospace Sciences Meeting

    Publication date :

    1985-01-01

    DOI :

    https://doi.org/10.2514/6.1985-207

    Type of media :

    Conference paper

    Type of material :

    Electronic Resource

    Language :

    English

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