02.2 - Experimental Aerodynamics
AN EXPERIMENT INVESTIGATION ON SHOCKINDUCED TURBULENT BOUNDARY LAYER SEPARATION FLOW-FIELD
X. Zhao¹, X. Xiang¹, L. Wei¹, Q. Shen¹; ¹China Academy of Aerospace Aerodynamics, China
To research the flowfield unsteadiness, the fast response Pressure Sensitive Paint (PSP) was developed which has the capability of undertaking global fluctuating pressure measurements. Visualization and measurements of aerodynamic effects on a blunt fin/flat plate configuration were conducted in a hypersonic wind tunnel. The dynamic pressure measurement results were provided in this paper.