Computational Analysis of Unsteady Circumferential and Radial Distortion in Subsonic Diffusers.
Final rept. 3 Nov 72-30 Jun 73,
ADVANCED TECHNOLOGY LABS INC WESTBURY N Y
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Two computational models of the unsteady flow in the subsonic diffuser section of an axisymmetric, external compression, supersonic inlet are described. The first pertains to the inviscid flow on a cylindrical stream surface through the diffuser, from the terminal shock to a discharge station representing the engine face. The equations of motion for a compressible gas are solved numerically by a second order finite difference technique. Several numerical examples are carried out to illustrate the capabilities of the computational model the results are discussed and interpreted in relation to the problem of experimental simulation of circumferential distortion. The second computational model pertains to the axisymmetric flow in meridional planes through the subsonic diffuser. Modified author abstract
- Fluid Mechanics