An experimental study of unsteady separated shock wave boundary layer interactions Export

@inproceedings{BruceExperimental, abstract = {An experimental investigation of the unsteady interaction between a turbulent boundary layer and a normal shock wave of strength M? = 1.4 subject to periodic forcing in a parallel walled duct has been conducted. Emphasis has been placed on the mechanism by which changes in the global flow field influence the local interaction structure. Static pressure measurements and high speed Schlieren images of the unsteady interaction have been obtained. The pressure rise across the interaction and the appearance of the local SBLI structure have been observed to vary during the cycle of periodic shock wave motion. The magnitude of the pressure rise across the interaction is found to be related to the relative Mach number of the unsteady shock wave as it undergoes periodic motion. Variations in the upstream Influence of the interaction are sensitive to the magnitude and direction of shock wave velocity and acceleration and it is proposed that a viscous lag exists between the point of boundary layer separation and the shock wave position. Further work exploring the implications of these findings is proposed, including studies of the variation in position of the points of boundary layer separation and reattachment. Conference code: 69861}, address = {Department of Engineering, University of Cambridge}, author = {Bruce, P. J. K. and Babinsky, H.}, citeulike-article-id = {1988414}, citeulike-linkout-0 = {http://www.scopus.com/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34250793846}, citeulike-linkout-1 = {http://www.scopus.com/scopus/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34250793846}, journal = {Collect. Tech. Pap. Aeros. Sci. Meet.}, keywords = {buffet, cambridge, experimental}, pages = {13795--13806}, posted-at = {2007-11-26 20:57:33}, priority = {4}, series = {45th AIAA Aerospace Sciences Meeting 2007}, title = {An experimental study of unsteady separated shock wave boundary layer interactions}, url = {http://www.scopus.com/scopus/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34250793846}, volume = {20} }

TY - CONF ID - BruceExperimental L3 - citeulike-article-id:1988414 N2 - An experimental investigation of the unsteady interaction between a turbulent boundary layer and a normal shock wave of strength M? = 1.4 subject to periodic forcing in a parallel walled duct has been conducted. Emphasis has been placed on the mechanism by which changes in the global flow field influence the local interaction structure. Static pressure measurements and high speed Schlieren images of the unsteady interaction have been obtained. The pressure rise across the interaction and the appearance of the local SBLI structure have been observed to vary during the cycle of periodic shock wave motion. The magnitude of the pressure rise across the interaction is found to be related to the relative Mach number of the unsteady shock wave as it undergoes periodic motion. Variations in the upstream Influence of the interaction are sensitive to the magnitude and direction of shock wave velocity and acceleration and it is proposed that a viscous lag exists between the point of boundary layer separation and the shock wave position. Further work exploring the implications of these findings is proposed, including studies of the variation in position of the points of boundary layer separation and reattachment. Conference code: 69861 JF - Collect. Tech. Pap. Aeros. Sci. Meet. SE - 45th AIAA Aerospace Sciences Meeting 2007 AD - Department of Engineering, University of Cambridge EP - 13806 TI - An experimental study of unsteady separated shock wave boundary layer interactions VL - 20 SP - 13795 KW - buffet KW - cambridge KW - experimental AU - Bruce, PJK AU - Babinsky, H UR - http://www.scopus.com/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34250793846 ER -