The development of a supersonic speed flight, one problem of practical importance is the inviscid/viscous interaction between shock wave and turbulent boundary layer. High local surface heat transfer could cause the burn-out of important units protruded into a supersonic flow field. Also, the large spatial difference of heating rates could bring a large thermal stress on a vehicle surface. For last decades, many researchers have tried to understand the flow structure and heat transfer phenomena near the protruding body in a supersonic flow. Aso[1] has measured pressure and heat flux distribution in the separated flow region by sharp fin and Stanton number is calculated from the measured heat flux. He showed the increase in pressure distribution and heat transfer in a separated and a reattachment flow region. However, this test needs a long test time for measuring two-dimensional distribution with 10 array sensors. Alvi[2] showed the sharp fin generating lambda-shock structure by using PLS (Planar Laser Scattering) imaging technique. But the investigation focused only on a shock visualization. Lu[3] proposed the correlation between a Mach number and an angle made by inviscid shock wave trace. But Lu’s experiment also did not contain the pressure and heat transfer distribution data either. Knight[4] has conducted the numerical simulation and the experiment for the backward of a sharp fin in supersonic turbulent flow. Rodi[5] has studied the comparison of pressure distributions between a sharp and a blunt fin. Even in this test, he failed to include the heat transfer distribution to the results. In this study, heat transfer near a sharp fin was investigated. The fin rotating angle is considered as a parameter. We took the surface temperature images using an infra-red camera for the turbulent flow separated regions near sharp fins. To satisfy the constant heat flux condition on a surface, we made a thin foil heater which can be installed to the bottom surface near the fin. For the understanding of flow characteristics around a fin, the oil-lampblack method was also conducted.
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Shigeru Aso, Masanori Hayashi and Anzhong Tan : The Structure of Aerodynamic Heating in Three-Dimensional Shock Wave/Turbulent Boundary Layer Interactions Induce by Sharp Fin and Blunt Fins. AIAA, 89-1854
F. S. Alvi and G. S. Settles : Physical Model of the Swept Shock Wave/Boundary-Layer Interaction Flow Field. AIAA Jouna , Vol. 30, No. 9, September 1992
F. K. Lu, G. S. Settles and C. C. Horstman : Mach Number Effects on Conical Surface Features of Swept Shock-Wave/Boundary-Layer Interactions, AIAA Jounal, Vol. 28, No. 1, January 1990
Doyle D. Knight, T.J. Garrison, G.S. Settles, A.A. Zheltovodov, A.I. Maksimov and A.M. Shevchenko, and S. S. Vorontsov : Asymmetric Crossing-Shock-Wave/Turbulent-Boundary-Layer Interaction, AIAA Jounal, Vol. 33, No. 12, December 1995
P. E. Rodi and D. S. Dolling : Behavior of Pressure and Heat Transfer in Sharp Fin-Induce Turbulent Interaction”, AIAA Jounal, Vol. 33, No. 11, November 1995
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Song, J., Yi, J., Yu, M., Cho, H., Hwnag, K., Bae, J. (2009). Experimental investigation of heat transfer characteristic in supersonic flow field on a sharp fin shape. In: Hannemann, K., Seiler, F. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-85181-3_72
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