A proof-of-concept study is performed for a supersonic channel-airfoil concept, which can be applied to the leading edges of wings, tails, fins, struts, and other appendages of aircraft, atmospheric entry vehicles, and missiles in supersonic flight. It is designed to be beneficial at conditions in which the leading edge is significantly blunted and the Mach number normal to the leading edge is supersonic. The supersonic channel-airfoil concept is found to result in significantly reduced wave drag and total drag (including skin-friction drag) and significantly increased lift/drag although maximum heat-transfer rate was increased for the geometries tested.


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    Title :

    Supersonic channel airfoils for reduced drag


    Additional title:

    Überschalltragflügel mit einer Schlitzöffnung zur Widerstandsreduzierung


    Contributors:
    Ruffin, S.M. (author) / Gupta, A. (author) / Marshall, D. (author)

    Published in:

    AIAA Journal ; 38 , 3 ; 480-486


    Publication date :

    2000


    Size :

    7 Seiten, 16 Bilder, 3 Tabellen, 19 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Supersonic Channel- Airfoils for Reduced Drag

    Ruffin, S. M. / Gupta, A. / AIAA | British Library Conference Proceedings | 1997


    Supersonic channel-airfoils for reduced drag

    Ruffin, Stephen / Gupta, Anurag | AIAA | 1997


    Supersonic Channel Airfoils for Reduced Drag

    Stephen M. Ruffin / Anurag Gupta / David Marshall | AIAA | 2000



    Aerothermodynamic Design of Supersonic Channel Airfoils for Drag Reduction

    Gupta, Anurag / Ruffin, Stephen M. | SAE Technical Papers | 1997