NASA NTRS · 19800039758
Calculation of inlet flow fields by an implicit technique
Abstract
Two-dimensional inlet flow fields in a supersonic free stream are calculated by an implicit, shock-capturing, finite-difference method. The Euler equations are subjected to a general curvilinear transformation and a body-fitted coordinate system is employed. The method is used to solve supercritical, critical, and subcritical flow fields which are simulated by prescribing appropriate conditions at the inlet outflow boundary. Results are presented for a drooped-cowl inlet.
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Biringen, S., Chaussee, D. S., Mcmillan, O. J.. 1980-01-01. Calculation of inlet flow fields by an implicit technique. https://ntrs.nasa.gov/citations/19800039758
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