A simple rugged acoustic stall sensor which has an output proportional to angle of attack near wing stall has been evaluated on a Cessna 319 aircraft. A sensor position has been found on the wing where the sensor output is only slightly affected by engine power level, yaw angle, flap position and wing roughness. The NASA LRC General Aviation Simulator has been used to evaluate the acoustic sensor output as a control signal for active stall deterrent systems. It has been found that a simple control algorithm is sufficient for stall deterrence.


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    Title :

    Investigation of a Stall Deterrent System Utilizing an Acoustic Stall Sensor


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    National Business Aircraft Meeting and Engineering Display ; 1977



    Publication date :

    1977-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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