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Flow structures around hypersonic TSTO launch vehicle were investigated by utilizing the electrical discharge method. First, boundary layers near the orbiter surface were observed by a visualization technique of boundary layers. Subsequently, lateral and cross-sectional shock shapes around TSTO launch vehicle were observed by a visualization technique of shock waves. From these results, it was confirmed that a separation shock wave was generated near the orbiter surface. In this study, the visualizations were carried out at Mach 10.

Study on Flow Structure around Hypersonic TSTO Launch Vehicle