The lacuna in addressing the fundamentals of compressible mixing layers subjected to pressure gradients in confined ducts motivated the current investigations. Studies are conducted on a canonical compressible mixing layer established between M1=2.0 and M2=1.5 flows within a suction type supersonic wind tunnel. Pressure gradients are imposed on the mixing layer by placing appropriate inserts on the test section walls. High speed schlieren visualizations and static pressure measurements are performed. Interesting shock-shear layer interactions are observed in the test section.
雑誌名
Proceedings. International Conference on Flow Dynamics
Investigations on Compressible Mixing Layers in Confined Ducts
srisha-paper-icfd2015.pdf
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