Transient behavior of supersonic flow through inletsA solution technique to compute inlet flow behavior is presented. The phenomena of inlet unstart and restart are investigated using a flux-split procedure applied to the Euler and Reduced Navier Stokes (RNS) equations. A time consistent direct sparse matrix solver in conjunction with a domain decomposition strategy is applied to compute the transient flow behavior both internal and external to the inlet. Time varying shocks and time varying recirculation regions are efficiently analyzed. The code is quite general and is suitable for the computation of flow for a wide variety of geometries and over a wide range of Mach and Reynolds numbers.
Document ID
19900055679
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pordal, H. S. (Cincinnati Univ. OH, United States)
Khosla, P. K. (Cincinnati Univ. OH, United States)
Rubin, S. G. (Cincinnati, University OH, United States)