Thrust vectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergent-divergent nozzle

Abstract

The transverse gas injection into the main supersonic §ow of an axisymmetric convergent-divergent (C-D) propulsive nozzle is investigated for the §uidic thrust vectoring (FTV) possibilities as the segment part of the CNES ¤Perseus¥ project. Truncated ideal contour and conical C-D nozzles with di¨erent position and angle of the secondary circular injection port are selected as test models in the current numerical and experimental study. Analytical approach revealed parameters which a¨ect the FTV e©ciency, these criterions are further numerically explored and results data of the conical nozzle test cases are compared and coupled with the ones from experiments. It is found that upstream inclined injection has positive e¨ect on vectoring capabilities and that with moderate secondary to primary mass- §ow ratios, ranging around 5%, pertinent vector side force is possible to be achieved. NOMENCLATURE AND ABBREVIATIONS2D two-dimensional 3D three-dimensional C d discharge coe©cient

Aircraft Thrust Vector Control Using Variable Vanes; Numerical Simulation and Optimization

“…This research has produced a three-dimensional, viscous network with the organization and considered two Baldwin-Lomax and A-K algebraic turbulence models. The effects of the angle of the divergent part of the nozzle and the injection location on the system's efficiency have been investigated [27][28][29][30].…”