Numerical investigation of the wall temperature effects on shock-wave turbulent boundary layer interactions

The shock-wave turbulent boundary layer interaction (STBLI) is an important phenomenon in many practically relevant high-speed flow applications such as re-entry vehicles, air-breathing engines, rocket nozzles, etc. STBLI occurs in supersonic flow near solid surfaces where a shock wave is generated or reflected. The complex interaction is typically characterized by boundary layer thickening, shock-induced separation, thermo-mechanical loading, and low-frequency unsteadiness. In high-speed aerospace applications, the effects of STBLI can lead to catastrophic failure during flight. For this reason, the accurate prediction of STBLI is crucial for the design of such applications. Although previous investigations have led to an improved understanding of several key features of STBLI, there are many aspects of the interaction which are still not fully understood. The present study uses large-eddy simulations to investigate the effect of wall temperature on the key features of STBLI, namely, the shock-induced separation, mechanical loading, and low-frequency unsteady behavior.

Grantor dc:publisher

University of Tennessee at Chattanooga

Author dc:creator

• Durant, Eli

Contributors dc:contributor

• Ranjan, Reetesh
• Sreenivas, Kidambi; Margraves, Charles; Elliott, Trevor
• College of Engineering and Computer Science

• Shock waves
• Turbulent boundary layer

Licence

• http://rightsstatements.org/vocab/InC/1.0/

Language dc:language

English, eng

Repository record dc:identifier

https://scholar.utc.edu/theses/846

OAI identifier oai:identifier

oai:scholar.utc.edu:theses-2023