Program developed for computing aerodynamic design of multistage axialflow compressor and associated blading geometry input for internal flow analysis. Aerodynamic solution gives velocity diagrams on selected streamlines of revolution at blade row edges. Program written in FORTRAN IV.
Design of Multistage Axial-Flow Compressors
NASA Tech Briefs ; 7 , 4
1983-10-01
Miscellaneous
No indication
English
Reverse flow in multistage axial compressors
AIAA | 1986
|Reverse flow in multistage axial compressors
AIAA | 1990
|Parametric study of advanced multistage axial-flow compressors
TIBKAT | 1967
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