An Approximate Method of Calculating the Performance of an Axial Compressor on the Basis of Its Geometry,
Abstract
A method, based on the cascade geometry, was derived to determine the parameters of individual stages and overall parameters of an axial compressor. The method employs generalized results obtained from aerodynamic tests of plane cascades used in axial compressors. The method was converted to the SAKO language for the ZAM-2 digital computer. A comparison of the parametric values determined by the derived method with experimental results showed close agreement of the findings. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 03, 1969
- Accession Number
- AD0865335
Entities
People
- Jan Traczyk
Organizations
- National Air and Space Intelligence Center