ROTOR BLADE DESIGN
Design of Two-Dimensional Supersonic Turbine Rotor Blades With Boundary-Layer Correction
A computer program has been developed for the design of supersonic rotor blades where losses are accounted for by correcting the ideal blade geometry for boundary layer displacement thickness. The computer program input consists essentially of the rotor inlet and outlet Mach numbers, upper- and lower-surface Mach numbers, inlet flow angle, specific heat ratio, and total flow conditions. The program gas properties are set up for air. Additional gases require changes to be made to the program. The computer output consists of the corrected rotor blade coordinates, the principal boundary-layer parameters, and the aftermixing conditions.
Program Size: 2,011 Statements
Computer Language: FORTRAN IV
Copyright (c) 1996 Pacific HiTech, Inc. and COSMIC 
