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theses

Shock-wave boundary-layer interaction (SBLI) has long been an important phenomenon in aerodynamics, from transonic through to hypersonic speeds. High-speed flow has been at the center of research for many applications such as the hypersonic flight engine (i.e., scramjet), aircraft (i.e., SR-72), re-entry vehicle (i.e., Space Shuttle), missile (i.e., BrahMos-II) and high-speed transportation (i.e., Hyperloop, Uber Elevate). As hypersonics is still an area of research, we need more reliable CFD models to predict the flow structures of the flows over complex geometries. For that purpose, available models should be validated in order to develop an understanding of a reliable computational model development approach for hypersonic flow. In the current research work, the assessment of the k−! Wilcox (2006) turbulence model to predict surface aerothermodynamic loading on a large hollow cylinder flare configuration for turbulent flows ranging from Mach 5 to 8 has been performed. Additionally, three Euler flux schemes, i.e., Roe, AUSM+ and HLLE+, have been evaluated along with a grid independence study. The experimental data from CUBRC has been used for validation of the numerical results. The surface pressure is consistently underpredicted and surface heat transfer is consistently overpredicted by the k − w Wilcox (2006) turbulence model. Also, an unphysical spike in turbulent kinetic energy is observed upstream of the reattachment location. The k − w turbulence model overpredicts the size of the separation region for all cases which is an important factor to be taken into consideration while designing control surfaces for hypersonic vehicles.

ETD_8774

M.S.

Includes bibliographical references

by Saumil B. Patel

doi:10.7282/T3H135F4

ETD graduate

The author owns the copyright to this work.