The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume II.
Final rept. 1 Jul 71-30 Jun 72,
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM) TURBOMACHINERY LAB
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The report describes the test results of a supersonic axial-flow compressor stage with a tip Mach number of 2.0. This volume discusses a method to eliminate the inlet problem. Author
- Jet and Gas Turbine Engines