Experimental and numerical study of the fluidic thrust vectoring of a two-dimensional supersonic nozzle

Fluidic thrust vectoring was used experimentally on an asymmetric supersonic nozzle to create a yaw moment. It implies a concept using two nozzles. The experiment took place in the R2-Ch blow-down facility of the ON ERA center of Chalais-Meudon and high performances were achieved. The Shock Vector Control is studied both numerically and experimentally on a Mach 1.36 asymmetric 2D nozzle model to highlight its potential performances and the influences of the parameters. The Reynolds Averaged Navier-Stokes code elsA is validated on a NASA experiment dealing with the Shock Vector Control of a Mach 2 nozzle. A new experiment of yaw-vectoring was realized in the blow-down test-facility R2-CH at the ONERA Center of Chalais-Meudon. The nozzle can be fluidically vectored thanks to two sonic injectors at the end of each wall. This paper focuses on the results of the Shock Vector Control Concept. The nozzle pressure ratio and the injected mass flow rates were varied. Despite the two close sidewalk whose developing boundary layers affect the Mach numbers, the computational results (2D RANS calculations with elsA) are in a close agreement with the experimental ones.