Aerodynamic heating phenomena in three-dimensional shock wave/turbulent boundary layer interactions induced by sweptback blunt fins

Shsgeru Aso, Seishi Kuranaga, Shigehide Nakao, Masanori Hayashi

研究成果: Contribution to conferencePaper査読

3 被引用数 (Scopus)

抄録

The detailed structure of aerodynamic heating phenomena in three-dimensional shock wave/turbulent boundary layer induced by sweptback blunt fins are revealed by a new method developed by the present authors. The new method is based on a new type of thin-film heat transfer gauge with high spatial resolution and fast response. The remarkable features of the structure of aerodynamic heating phenomena and significant change of higher heating regions with sweep angles of the blunt fins in three-dimensionaI shock wave/turbulent boundary layer interaction region are obtained. The results provide valuable information not only to the understanding of the three-dimensional shock induced aerodynamic heating phenomena but also design of spaceplanes and winged vehicles-Experiments are performed under the testing conditions of Mach number of 4, wall temperature condition Tw/To of 0-65 and Reynolds number of 1.2x107. The sweptback blunt fins with semi-cylindrica1 leading edge in the plane normal to it are used for the present experiments. Sweep angles are selected as 0, 15, 30, and 45 degrees and placed normal to the flat plate model. The flow fields are visualized by oil flow technique and detailed surface pressure and surface heat flux distributions in the interaction regions for various sweptback fins are measured.

本文言語英語
出版ステータス出版済み - 1 1 1990
イベント28th Aerospace Sciences Meeting, 1990 - Reno, 米国
継続期間: 1 8 19901 11 1990

その他

その他28th Aerospace Sciences Meeting, 1990
国/地域米国
CityReno
Period1/8/901/11/90

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学

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