Accession Number:
AD0752585
Title:
The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume I.
Descriptive Note:
Final rept. 1 Jul 71-30 Jun 72,
Corporate Author:
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
Personal Author(s):
Report Date:
1972-06-01
Pagination or Media Count:
51.0
Abstract:
The report describes the test results of a supersonic axial flow compressor stage with a tip Mach number of 2.0. Volume I discusses especially the inlet stall, the associated flow field and the stage performance. Methods are proposed to eliminate the stall problem. Author
Descriptors:
Subject Categories:
- Jet and Gas Turbine Engines