An airfoil is reported that has an upper surface shaped to control flow accelerations and pressure distribution over the upper surface to prevent separation of the boundary layer due to shock wave formulation at high subsonic speeds well above the critical Mach number. A highly cambered trailing edge section improves overall airfoil lifting efficiency.


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    Titel :

    Airfoil Shape for Flight at Supersonic Speeds


    Beteiligte:
    R. T. Whitcomb (Autor:in)

    Erscheinungsdatum :

    1971


    Format / Umfang :

    27 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    Whitcomb, R. T. | NTRS | 1976


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    Miles, J.W. | Engineering Index Backfile | 1947


    Economy of flight at supersonic speeds

    Jones, R. T. | NTRS | 1976