Investigation of the pseudo-shock wave in a two-dimensional supersonic inlet

Abstract

This paper describes experimental and numerical investigations into the multiple shock waves/ turbulent boundary layer interaction in a supersonic inlet. The test model has a rectangular shape with an asymmetric subsonic diffuser of 5°. Experiments were conducted to obtain the visualization images and static pressure data by using supersonic wind tunnel. Numerical simulation was performed by solving the RANS equations with the Menter's SST turbulent model. The inflow condition was a free-stream Mach number of 2.5 and a unit Reynolds number of 7.6 9 10 7 /m. Numerical results showed good agreement with the experimental results. Based on this agreement, the flow characteristics which are often very difficult to obtain experimentally alone were analyzed with the aid of numerical simulation. The structures, pressure and velocity distributions, and total pressure loss of the pseudo-shock wave in the supersonic inlet were presented in detail from flow visualization images and static pressures.

Experimental Investigation on Boundary Layer Control and Pressure Performance for Low Reynolds Flow with Chemical Reaction

“…Chen et al [19,20] numerically simulated the shock string phenomenon of a diffuser in a supersonic wind tunnel with a pressure recovery system and analyzed the formation mechanism of shock strings and typical flow structures with relatively fine two-dimensional grid calculation results. Lee et al [21] described experimental and numerical investigations into the multiple shock wave-turbulent boundary layer interaction in a supersonic inlet. Fan et al [22] designed a free-jet hypersonic wind tunnel diffuser with a diameter of Φ240 mm and Mach number of 6.0 and determined the optimal design scheme of the diffuser by comprehensively considering the quality of the wind tunnel flow field, the diffuser's anti-pressure capability, the diffuser's total pressure recovery, and other indicators.…”

Application of Mach-Zehnder interferometers for isolator shock trains

“…In addition, from studies conducted mainly in the Japanese research institutions including Kyushu University, Tokyo Institute of Technology, and Muroran Institute of Technology, it is widely recognized that a shock train oscillates across its time-mean position and extreme pressure fluctuation caused by the shock train oscillation, induces vibration of the machineries or causes heavy sound noise to be emitted into the atmosphere [2]. In recent years, the physics on the behavior of an unsteady shock train has attracted much attention from researcher community engaged in the design of scramjet engines all over the world [3][4][5][6][7][8][9], because higher engine thrust can be achieved if a shock train is confined to the isolator of the scramjet engine and shock train oscillations have a significant effect on the unstart of the engine.…”