Calculated responses of symmetrical airplane motions, wing deformations, and wing loads due to continuous turbulence are shown to compare favorably with available flight-test results. These calculated responses are based on random-process theory, five degrees of freedom, lifting-surface aerodynamics, and one-dimensional turbulence. Of the five degrees of freedom used only three, rigid-body translation and pitch modes and the first wing bending mode, are shown to contribute significantly to the airplane responses over the frequency range considered (0 to 2 cps). Bending-moment amplification factors are presented in order to show the effects of dynamic aeroelasticity. These effects are found to increase the response by 35 to 115 percent, depending upon the spanwise station. (Author)


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    Title :

    Calculated Responses of a Large Sweptwing Airplane to Continuous Turbulence with Flight-Test Comparisons


    Contributors:
    F. V. Bennett (author) / K. G. Pratt (author)

    Publication date :

    1960


    Size :

    28 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English