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Aerodynamic Heating in Three-Dimensional Shock Wave Turbulent Boundary Layer Interaction Induced by Sweptback Sharp Fins in Hypersonic Flows
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English
Abstract
For the fundamental study of aerodynamic heating of winged vehicle and space planes in hypersonic flow the detailed structure of three-dimensional shock wave/turbulent boundary layer interaction region induced by sweptback sharp fins are investigated carefully by oil flow technique and pressure distribution. The major objectives of the present study are to study the effects of the shape of the leading edge of the fin to the flow fields on the body and to study the effect of the sweep angle of the leading edge of the fin to the interaction region. Also aerodynamic heating phenomena in the flow fields are investigated by using a new technique. For the measurements a new method of measuring heat flux developed by the present authors are used. The new method is based on a new type of thin-film heat transfer gauge with high spatial resolution and fast response. The results suggest the effects of the shape of the leading edge to the flow fields are quite significant and the sweep of the leading edge of the fin to freestream is quite important to reduce the interaction region.
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Citation
Aso, S., Maekawa, S., and Hayashi, M., "Aerodynamic Heating in Three-Dimensional Shock Wave Turbulent Boundary Layer Interaction Induced by Sweptback Sharp Fins in Hypersonic Flows," SAE Technical Paper 912044, 1991, https://doi.org/10.4271/912044.Also In
References
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- Aso, S. Tan, A. Hayashi, M. The structure of aerodynamic heating in three-dimensional Shock Wave and Turbulent Boundary Layer interactions Induced by Sharp Fins and Blunt Fins AIAA Paper 89-1854 1989
- Aso, S. Kuranaga, S. Nakao, S. Hayashi, M. Aerodynamic Heating Phenomena in Three-Dimensional SHock Wave/Turbulent Boundary Layer Interaction induced by Sweptback Fins AIAA Paper 90-0381 1990
- Hayashi, M. Sakurai, A. Aso, S. A Study of a Multi- Layered Thin Film Heat Transfer Gauge and a New Method Measuring Heat Transfer Rate with It Transactions of the Japan Society for Aeronautical and Space Sciences 30 88 1987 91 101
- Hayashi M. Aso S. Tan A. “Fluctuation of Heat Transfer in Shock Wave/Turbulent Boundary-Layer Interaction AIAA J. 27 4 April 1989 399 404