Aerodynamic drag analysis in hypersonic jet-induced flowfields using similarity criteria

Based on jet momentum similarity, the applicability of conventional hypersonic wind tunnels operating at a freestream total pressure of 2 MPa and total temperatures ranging from 500 K to 900 K was investigated for simulating jet interaction flowfield aerodynamic drag under representative low-altitude, high-speed conditions ( H = 0.1 km, Ma = 5). The compressible Navier-Stokes equations were solved using the SST turbulence model. Analysis of wind tunnel freestream total temperature, cold jet simulation, and jet temperature settings revealed that jet momentum exhibits considerable applicability under conventional hypersonic wind tunnel conditions. Within the 500–900 K total temperature range, maximum drag deviation induced by total temperature variation was merely 0.669 %, while cold jet simulation could be adopted as a simplified investigative approach. And it was consequently found that, under certain conditions, the separation shock position in the flow field shifts rearward correspondingly with an increase in either the freestream Reynolds number or the jet-to-freestream energy ratio.