Effect of Aft Wall Offset on Supersonic Flow over Cavity

Autor:	C. Rajeev, R. R. Vinil Kumar, Aravind Vaidyanathan, Praveen Kumar Maurya
Rok vydání:	2016
Předmět:	Materials science Offset (computer science) Physics::Optics Mechanics Physics::Fluid Dynamics symbols.namesake Shear layer Cavity flow Boundary layer Mach number Schlieren symbols Physics::Accelerator Physics Thickening Choked flow
Zdroj:	Fluid Mechanics and Fluid Power – Contemporary Research ISBN: 9788132227410
DOI:	10.1007/978-81-322-2743-4_5
Popis:	A study is conducted on supersonic flow at Mach number 1.65 over rectangular cavity of length-to-depth (L/D) ratio 3. Schlieren visualization revealed normal shock train like pattern in flow over the cavity. These shock structure are unsteady, and oscillated longitudinally inside the test section over the cavity. The oscillating shock train is eliminated, as the blockage produced by shear layer and boundary layer thickening due to pressure recovery in cavity is reduced by offsetting the cavity aft wall. The shock train—shear layer coupling is observed to completely suppress the third and higher modes of cavity oscillations.
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=doi_________::af85b19051117afe1b4c1282c7fb052e https://doi.org/10.1007/978-81-322-2743-4_5 Zobrazit plný text záznamu