Accession Number:

ADP006217

Title:

Experimental Investigation of a Supercritical Compressor Rotor Blade Section,

Descriptive Note:

Corporate Author:

DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V COLOGNE (GERMANY F R)

Report Date:

1987-09-01

Pagination or Media Count:

11.0

Abstract:

A controlled diffusion rotor blade section was designed for a supercritical inlet Mach number of M10.85 and a flow turning of 20. The blade section has been tested in a cascade wind tunnel under various inlet flow conditions and axial velocity density ratios. Detailed investigation about transition and separation points were carried out at the design and at two off design inlet flow conditions. The results are presented and discussed.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE