A complete set of linear stability and control derivatives of the F-111A airplane was determined with a modified maximum likelihood estimator. The derivatives were determined at wing sweep angles of 26 deg, 35 deg, and 58 deg. The flight conditions included a Mach number range of 0.63 to 1.43 and an angle of attack range of 2 deg to 15 deg. Maneuvers were performed at normal accelerations from 0.9g to 3.8g during steady turns to assess the aeroelastic effects on the stability and control characteristics. The derivatives generally showed consistent trends and reasonable agreement with the wind tunnel estimates. Significant Mach effects were observed for Mach numbers as low as 0.82. No large effects attributable to aeroelasticity were noted.


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    Title :

    Flight-Determined Stability and Control Coefficients of the F-111A Airplane


    Contributors:
    K. W. Iliff (author) / R. E. Maine (author) / S. T. Steers (author)

    Publication date :

    1978


    Size :

    91 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Flight-determined stability and control coefficients of the F-111A airplane

    Iliff, K. W. / Maine, R. E. / Steers, S. T. | NTRS | 1978




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