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
01.10.1983
Sonstige
Keine Angabe
Englisch
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