抄録
Fuel Consumption at cruise conditions for hypersonic vehicles is one of the major criteria in the nozzle definition process Accurate estimation of the nozzle performances and the internal flow behavior are important. First step of the study consist in an evaluation of the geometrical design parameter influences on flow and thrust coefficients with 2D EULAR solver. Compatibility with requested thrust along the climb and the cruise, must be checked. 2D EULAR + boundary layer were carried out. Last step of the design process was supported by 3D EULAR and 3D NAVIER-STOKES. Mach 5 nozzle definition was tested in measurements and upstream total and static pressure screening. Comparison between predictions and test results validate the numerical design means. The numerical results will give helpful elements to get better understanding of phenomena in 2D nozzle.
