An overset grid approach was adopted for the computational fluid dynamics (CFD) simulations of internal flow in a diverging S-duct. NASA's OVERFLOW code was employed to investigate internal flow phenomena as well as establish the criteria for the convergence of CFD solutions based on flow conditions, turbulence models and grid size. Reynolds-averaged Navier-Stokes calculations were performed at two flight conditions with Mach numbers of0.6 and 0.3. The computational results were compared to experimental measurements of boundary layer profiles, wall pressure ratios, total pressure recovered and pressure distortion on the aerodynamic interface plane. Additional findings include flow separation and secondary flows which produce vortices inhibiting uniform flow and promoting pressure distortions through the S-duct.
|Commitee:||Chen, Hsun-Hu, Gea, Lie-Mine|
|School:||California State University, Long Beach|
|School Location:||United States -- California|
|Source:||MAI 52/01M(E), Masters Abstracts International|
|Subjects:||Aerospace engineering, Mechanical engineering|
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