Recent mishaps and incidents on Class IV aircraft have shown a need for establishing quantitative longitudinal high angle of attack (AOA) pitch control margin design guidelines for future aircraft. NASA Langley Research Center has conducted a series of simulation tests to define these design guidelines. Flight test results have confirmed the simulation studies in that pilot rating of high AOA nose-down recoveries were based on the short-term response interval in the forms of pitch acceleration and rate.


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    Title :

    Pitch control margin at high angle of attack - Quantitative requirements (flight test correlation with simulation predictions)


    Contributors:
    Lackey, J. (author) / Hadfield, C. (author)


    Publication date :

    1992-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English