Experimental study of the shock wave influence on adiabatic wall temperature in a supersonic air-droplet flow

Abstract

Abstract The results of an experimental study of the thermal parameters of a supersonic flow around a flat wall in the presence of finely divided water droplets are presented. The relative mass flow rate of the liquid (mass concentration) varied in the range 0.05-0.5%. Liquid (distilled water) was sprayed through centrifugal nozzles into the air flow in the prechamber of the supersonic wind tunnel. Next, the adiabatic wall temperature for the given flow conditions was measured with the use of infrared thermal imager. The input flow Mach number was 2.5, the Reynolds number based on the dynamic boundary layer length from the nozzle throat was at least 2·107 at the nozzle exit section. The research was performed at the experimental facilities of the Institute of Mechanics of Lomonosov Moscow State University.