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 Can Aeronautics and Space J May 1966 v 12 n 5 p 177-88)


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    Title :

    Stability and control considerations for STOL aircraft


    Additional title:

    AGARD -- Report


    Contributors:

    Published in:

    Publication date :

    1965


    Size :

    36 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    Stability and control considerations for STOL AIRCRAFT.

    Anderson, S. B. / Innis, R. C. / Quigley, H. C. | NTRS | 1966


    Stability and control considerations for STOL AIRCRAFT.

    Anderson, S. B. / Innis, R. C. / Quigley, H. C. | NTRS | 1965


    Stability and control considerations for STOL aircraft

    Anderson, S.B. / Quigley, H.C. / Innis, R.C. | Engineering Index Backfile | 1966


    Stability and control considerations for STOL AIRCRAFT

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


    Airworthiness considerations for STOL aircraft

    Holzhauser, C. A. / Innis, R. C. / Quigley, H. C. | NTRS | 1970