Experimental Investigation of Two Blunt-Trailing-Edge Supersonic Compressor Rotors of Different Blade Thicknesses and with Polynominal Camber Line

摘要

Two configurations of blunt-trailing-edge supersonic compressor blades incorporating a polynomial camber line were tested with air in a compressor rig. The performance of these blades was investigated over the speed range from 50 to 100 percent of design speed. The performance at the two blade configurations is compared, and the effect of the modifications between the two configurations is evaluated. A comparison of selected performance data obtained with circular arc blading tested previously and the polynomial camber blading is made to evaluate the effects of the camber redistribution. (Author)