Force and moment coefficients computed from test data are presented. Data indicate that, with respect to elevator-angle variation with speed, airplane will become unstable at approximately 0.7 Mach number. Two devices for improving longitudinal control, a wing-profile modification and auxiliary control flaps, increase the Mach number at which this instability occurs. Former device increases it by as much as 0.075 and 0.8 Mach number, their over- all characteristics are less favorable than those of wing-profile modification.


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    Title :

    Longitudinal Characteristics and Aileron Effectiveness of a Midwing Airplane from High-Speed Wind-Tunnel Tests


    Contributors:
    C. F. Hall (author) / R. L. Mannes (author)

    Publication date :

    1944


    Size :

    74 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Wind tunnel tests on aileron loads

    Bradfield, F. B. ;Midwood, G. F. ;Hounsfield, F. R. C. | SLUB | 1932


    Wind tunnel tests on aileron loads

    Bradfield, F. B. / Midwood, G. F. / Hounsfield, F. R. C. | TIBKAT | 1932