Accession Number : AD1001834


Title :   Investigation of 3D Shock-Boundary Layer Interaction: A Combined Approach using Experiments, Numerical Simulations and Stability Analysis


Descriptive Note : Technical Report,15 Jul 2014,14 Jul 2015


Corporate Author : UNIVERSITY OF ARIZONA Tucson United States


Personal Author(s) : Little,Jesse ; Fasel,Hermann ; Gross,Andreas


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/1001834.pdf


Report Date : 02 Dec 2015


Pagination or Media Count : 30


Abstract : The characteristics of impinging oblique shock turbulent boundary layer interaction (SBLI) are examined using experiments, simulations and stability analysis. The experimental focus is on application of stereoscopic particle image velocimetry (PIV) to the flow field produced by an impinging shock (produced by a 15 degree wedge) that is swept at angles of 0, 22.5, and 40 degrees in Mach 2.3 flow. The interaction length isfound to decrease with increasing sweep angle across the test matrix. The 22.5 degree and unswept case have cylindrical similarity and the 40 degree interaction appears conical. All cases show separated flow in the interaction region and most contain reverse flow that is clearly outside ofthe measurement uncertainty. A corresponding numerical SBLI study is undertaken for a laminar approach boundary layer at Mach 2.0. The skin friction and pressure distribution from the simulations are compared to experimental measurements and numerical results available in the literature. The response to lowamplitude disturbances is investigated in order to study the linear stability behavior of the separation bubble. The effects of the shock incidence angle and Reynolds number are also investigated. Threedimensional simulations are performed in order to explore transition.


Descriptors :   TURBULENT BOUNDARY LAYER , SIMULATIONS , SUPERSONIC WIND TUNNELS , HYPERSONIC FLOW , SHOCK


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE