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.
Experimental investigation of novel VTOL thrust vectoring nozzle
J Aircraft
Journal of Aircraft ; 2 , n 4
1965
6 pages
Article (Journal)
English
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