Preliminary Investigation of a Blunt Trailing Edge Blade Cascade in the S-3 Supersonic Cascade Tunnel

摘要

A 2/3 scale model of the R-32 rotor midsection was tested in a supersonic cascade tunnel of 6 x 5 cm test section. These tests were conducted at nominal freestream Mach number of 1.5 and 1.7, incidence angles were varied from +7 to -10 degrees, total inlet pressure from 1.5 to 3.0 kg/sq cm abs. No exhaust diffusor was used and only the static pressure distribution along the blade is measured. These tests demonstrated that there is no problem in starting the supersonic flow inside the passage. The existence and location of the 'pipe flow' configuration is strongly influenced by the back pressure and therefore the cascade can behave as an accelerating or decelerating one. (Author)