Pressure distributions on nozzle block of two-dimensional, oblique-exit-plane nozzle with turbulent flow were predicted and experimentally measured; thrusts, thrust vectors, and torques were calculated from pressure distributions; performance characteristics were strongly dependent upon plenum and ambient pressures and upon exit plane orientations; because of exit plane area changes, axial and lateral thrusts were found to exceed symmetric nozzle thrust values for certain conditions; results were predicted well by theory of characteristics and Gadd's formula for flow separation; at high altitudes, torque that can be obtained may be useful for maneuvering.
Thrust vectoring produced by supersonic nozzle with oblique exit plane
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 10
1966
4 pages
Article (Journal)
English
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