Based on assumption that aerodynamic forces acting at any point on lifting surface are linearly dependent upon local angle of attack at that point, theory of pure rolling motion is applied to experimentally observed motion of finned missile in supersonic flight.


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    Title :

    Method of determining some aerodynamic coefficients from supersonic free-flight tests of rolling missile


    Additional title:

    J Aeronautical Sciences


    Contributors:

    Published in:

    Publication date :

    1950


    Size :

    13 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :