Experimental study of pressure and temperature variations in a supersonic air flow through a flat channel

In this paper, the experimental dependences of static pressure and temperature on time and distance for channel flow are presented and analyzed. The choice of channel geometry is determined by the fact that a backward-facing step can be considered as a convergent-divergent diffuser, air duct, combustion chamber, etc. The experiments are carried out on a supersonic short-term aerodynamic setup with airflow at Mach numbers of 5 and 6. The obtained data are compared with the results of similar wind-tunnel tests in an axisymmetric case. For flat-channel flows, the recirculation zone occurs only behind the step. No other recirculation zones are observed due to the sufficient increase in transverse velocity along the channel. At the same time, the longitudinal velocity decreases, which leads to an increase in the static pressure. Thus, the intensity of the reflected shock waves abruptly becomes weaker, so that no other recirculation zones appear in the flow. The obtained temperature distributions in the near-wall zone at air deceleration during the flow over a backward-facing step at the considered flow velocities are found to have a minimum. The temperature then increases due to significant flow deceleration.

Keywords

Authors

References