Unsteady separated boundary layer in a transonic diffuser flow with self-excited oscillationsA numerical investigation of two-dimensional unsteady boundary layer in a transonic diffuser flow with self-excited oscillations and strong flow separation by solving the compressible, Reynolds-averaged, thin-layer Navier-Stokes equations with two-equations turbulence model is described. Three different meshes with constant streamwise mesh distribution and varying vertical mesh distribution were used. Results obtained indicate that a refinement of mesh studied here has minimal effect on the mean boundary layer flow but significantly increases the amplitude of oscillation of all flow variables. Comparisons of unsteady wall pressure, velocity profile, terminal shock, and separation pocket among computations and with experiment are presented.
Document ID
19860053673
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hsieh, T. (U.S. Navy, Naval Surface Weapons Center Silver Spring, MD, United States)
Coakley, T. J. (NASA Ames Research Center Moffett Field, CA, United States)