The report presents the key results of a model wing tunnel test program that was directed towards investigating the use of cyclic pitch propellers as the low speed longitudinal control system of a four propeller V/STOL tilt wing transport-type aircraft. The almost linear pitch control effectiveness of this system through transitional flight and in-ground effect along with the correlation with theory is discussed, and the moderate power increase associated with its use is shown. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Cyclic Pitch Control on a V/STOL Tilt Wing Aircraft


    Contributors:

    Publication date :

    1971


    Size :

    114 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Forward Swept Tilt Wing V/STOL Aircraft

    SAE / American Helicopter Society / AIAA | British Library Conference Proceedings | 1997


    Forward Swept Tilt Wing V/STOL Aircraft

    SAE / American Helicopter Society / AIAA | British Library Conference Proceedings | 1997


    Report on stability and control testing of tilt wing V/STOL aircraft

    Longhurst, W.S. | Engineering Index Backfile | 1966



    Twin tilt nacelle V/STOL aircraft

    Eskey, M. A. / Wilson, S. B., III / Valckenaere, W. et al. | NTRS | 1984