Expressions for damping derivatives derived by means of linearized theory; wing represented by unknown distribution of doublets; integral equation containing unknown distribution is set up and solved by analogy with known incompressible flow relations.


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    Title :

    Damping in pitch and roll of triangular wings at supersonic speeds


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:
    Brown, C.E. (author) / Adams, M.C. (author)


    Publication date :

    1948


    Size :

    29 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :