Experimental Study on Separation Shock Wave Unsteadiness in Hypersonic Shock Wave/Boundary Layer Interaction
The objective of the study is to investigate the relevance between unsteadiness of a separation shock wave motion and the state of a boundary layer downstream of hypersonic ramp-induced shock wave/boundary layer interaction. Little is known about the unsteady nature of the hypersonic interaction, while it has been known that supersonic turbulent interactive flows are inherently unsteady. Experiments were conducted on a flat plate with an aft-mounted ramp in a gun tunnel. Test Mach number was 10, Reynolds number was 2. 7 × 106 m-1, the attack angle of the model was zero, and the ramp deflection angle was varied from 18 to 30 deg. The flow behavior was studied using high speed schlieren images as well as spectral analysis of surface heat transfer. The state of boundary layers reattaching on the ramp surface was determined from heat transfer data. The experimental results show that there were low frequency fluctuations not only in size of a separation bubble but also in strength of heat transfer signals only when the reattaching boundary layers were transitional to turbulence. The frequency range of the oscillation of heat transfer signals was similar to that of the unsteady shock wave motion.
hypersonic flow shock wave/boundary layer interaction unsteadiness transition to turbulence
Hajime Itoh
Department of Aerospace Engineering, National Defense Academy, Yokosuka 2398686, Japan
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
199-202
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）