極超音速流中の衝撃波/境界層干渉場に関する放電発光法による研究 Study on Flowfield of Hypersonic Shock-Wave/Boundary-Layer Interaction by Electric Discharge Method
Investigations on the spatial flowfield of hypersonic shock-wave/boundary-layer interaction have been performed by utilizing the electric discharge method. The model geometry used in this experiment is composed of a flat plate and a fin. In general, visualizations of such spatial flowfield were very difficult or impossible. However, in these investigations utilizing the electric discharge method which is the method for visualizing three dimensional hypersonic flowfield phenomena, the spatial flowfield phenomena could be visualized qualitatively. The experiment is carried out using a hypersonic gun tunnel whose main characteristics are that the Mach number is 10 and the duration is 10ms.
- 日本航空宇宙学会誌 = Journal of the Japan Society for Aeronautical and Space Sciences
日本航空宇宙学会誌 = Journal of the Japan Society for Aeronautical and Space Sciences 46(534), 413-419, 1998-07