Rotor Performance of the R32-II Blunt Trailing Edge Blade Supersonic Compressor

摘要

A second supersonic compressor R32-II is designed and tested. The basic design ideas, in view of the experience gained with the R32-I wheel, and the overall and detail performance are given. A study is made of the downstream mixing with its influence on outlet flow angle, axial Mach number and total pressure distribution. A comparative study is made between the two wheels. (Author)