Transverse gas injection into a divergent section of a convergent-divergent rocket nozzle have been investigated for thrust vectoring effects as the segment part of the CNES P erseus program. Cold flow experiments on conical and truncated ideal nozzles have been conducted in the hypersonic windtunnel EDIT H. These experiments are compared and complemented by the numerical investigation results of the compressible FANS numerical solver CP S C. Number of parameters and performance criteria have been examined and reported. It is found that pertinent vector force is possible to be achieved via such fluidic thrust vectoring system.

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