NASA NTRS · 19800057445
A simplified shock-fitting solution to a supersonic internal corner flowfield
Abstract
A simplified shock-fitting method is developed and applied to a supersonic internal corner flowfield. An analytical approach is discussed, and results for a case with a free-stream Mach number of 2.47 and wedge angles of 12.2 deg are shown.
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Martin, J. A.. 1980-07-01. A simplified shock-fitting solution to a supersonic internal corner flowfield. https://ntrs.nasa.gov/citations/19800057445
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