A wind tunnel investigation of concepts to improve the high angle-of-attack stability and control characteristics of a high performance aircraft was conducted. The effect of vertical tail geometry on stability and the effectiveness of several conventional and unusual control concepts was determined. These results were obtained over a large angle-of-attack range. Vertical tail location, cant angle and leading edge sweep could influence both longitudinal and lateral-directional stability. The control concepts tested were found to be effective and to provide control into the post stall angle-of-attack region.


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    Title :

    Exploratory Low-Speed Wind-Tunnel Study of Concepts Designed to Improve Aircraft Stability and Control at High Angles of Attack


    Contributors:
    D. E. Hahne (author)

    Publication date :

    1985


    Size :

    73 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Experimental Study of Aircraft Stability Enhancement at High Angles of Attack

    Huang, A. / American Institute of Aeronautics and Astronautics / International Council of Aeronautical Sciences | British Library Conference Proceedings | 1996