Two-dimensional corner-expansion thrust vectoring nozzle, in which thrust vectoring is achieved by rotation of single vane was designed for high supersonic VTOL/STOL aircraft by Northrop Corp; thrust coefficient in excess of 0.97 was demonstrated in VTOL mode and throughout transition at nozzle pressure ratios typical of turbojet engines considered for applications; thrust coefficient in excess of 0.96 was attained in horizontal cruise mode down to nozzle pressure ratio of 3.5; this is particularly significant when considering that design pressure ratio of nozzle was 21; effective thrust vectoring was also demonstrated.


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    Title :

    Experimental investigation of novel VTOL thrust vectoring nozzle


    Additional title:

    J Aircraft


    Contributors:
    Hall, G.R. (author)

    Published in:

    Publication date :

    1965


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






    Thrust vectoring apparatus for jet VTOL aircraft

    KIM HYUNG OH / KIM KI BEOM | European Patent Office | 2019

    Free access