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.
|出版物ステータス||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 1990 → 1 11 1990
|その他||28th Aerospace Sciences Meeting, 1990|
|期間||1/8/90 → 1/11/90|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering