Studies of STOL aircraft show that relatively high maximum lift-coefficients and large increases in lift due to power are within present state of art; with these lift characteristics, approach speeds of order of 60 knots for aircraft of moderate wing loading can be realized; full advantage of STOL performance of aircraft may not be realized on routine operational basis, however, without some form of damping augmentation system because of lateral-directional handling considerations, particularly for large aircraft operating under instrument flight conditions; satisfactory characteristics can be obtained by use of only servodriven rudder. (See also AGARD -- Report 504 June 1965 36 p)


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    Title :

    Stability and control considerations for STOL aircraft


    Additional title:

    Can Aeronautics Space J


    Contributors:


    Publication date :

    1966


    Size :

    12 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Stability and control considerations for STOL AIRCRAFT.

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    Stability and control considerations for STOL AIRCRAFT

    ANDERSON, S. / INNIS, R. | AIAA | 1965


    Stability and control considerations for STOL AIRCRAFT.

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    Airworthiness considerations for STOL aircraft

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    V/STOL aircraft structural considerations

    Alvey, V.W. / Fried, H. | Engineering Index Backfile | 1966