Open AccessMitigation of shockwave induced boundary layer separation through a secondary recirculation duct in a hypersonic flow
Author(s) -
Kiran Joy Irimpan,
Anand Raj Hariharan
Publication year - 2021
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/1132/1/012024
Subject(s) - freestream , mach number , boundary layer , hypersonic speed , flow separation , mechanics , separation (statistics) , duct (anatomy) , shock wave , bubble , materials science , boundary layer control , jet (fluid) , aerospace engineering , environmental science , physics , reynolds number , engineering , computer science , medicine , pathology , machine learning , turbulence
A secondary recirculation duct which leaks fluid from a high pressure reattachment zone to a low pressure upstream location of a shock wave boundary layer interation zone is discussed in the below article. The mitigation can be attributed to both suction and blowing. Computational analyses of the above problem at a freestream of Mach 8.6 with various jet injection locations were studied for its effectiveness via a commercial software ANSYS Fluentl9 and the results are very promising. The jet injection close to the separation point is found to be most effective in delaying separation and reducing the separation bubble.