NASA NTRS · 19880000291
Unsteady Flow In A Supersonic Cascade With Shocks
Abstract
Operating range of turbomachinery for which stability calculated extended. TIPS (Two In-Passage Shocks) calculates unsteady lifts and moments on compressor blade if relative mach number supersonic and if two shock waves in blade passage. Written in FORTRAN IV and run on IBM 3033 with 370TSS operating system.
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Molls, Frank B., Braun, Willis H.. 1988-05-01. Unsteady Flow In A Supersonic Cascade With Shocks. https://ntrs.nasa.gov/citations/19880000291
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