Development of TPS (Thermal Protection System), such as thermal protection tile, is required to realize human space transportation. The tile size and a gap between tiles become important parameter since flow-field around tiles strongly depends on it. Then, Shock-Boundary-Layer Interaction (SBLI) is an inevitable problem for multistage space transportation vehicle such as TSTO (Two-Stage-To-Orbit), and it may occurs at the damaged tile (Crack) or a gap. Therefore it is necessary to investigate the effect of SBLI on heat flux around there at hypersonic speed. In this study, the effects of crack, where SBLI occurs, were investigated for TSTO hypersonic speed (M_∞=8.1).A square crack locates at SBLI point on the TSTO booster. Results show that a crack and its depth strongly effect on peak heat flux and aerodynamic interaction flow-field. In the cases of shallow crack (d/C=0.10), there exist two high heat flux regions on crack floor, which locates at a flow reattachment region and a back end wall of crack. In this case, a peak heat flux at flow reattachment region becomes about 2 times as large as the stagnation point heat flux, which value becomes larger compared with a peak heat flux in the case of No-Crack TSTO. While in the case of deep crack (d/C=0.20), overall heat flux on crack floor decreases to below the stagnation point heat flux.%本研究では，二段式宇宙往還機(TSTO: Two-Stage-To-Orbit)に対し，Crack部（機体損傷部，耐熱タイル剥落部）において衝撃波•境界層干渉部が起きた場合，Crack内部の詳細な流れ場の解析と空力加熱率への影響について調べた.以下に得られた結果をまとめる.
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机译：为了实现人类空间运输，需要开发TPS（热保护系统），例如热保护砖。瓦片大小和瓦片之间的间隙成为重要参数，因为瓦片周围的流场强烈地依赖于它。因此，冲击边界层相互作用（SBLI）对于诸如TSTO（两阶段进入轨道）之类的多级空间运输车辆而言是不可避免的问题，它可能发生在损坏的瓦片（裂缝）或间隙处。因此，有必要研究SBLI对高超声速附近热流的影响。本研究以TSTO高超声速（M_∞= 8.1）研究了SBLI发生裂纹的影响。方形裂纹位于TSTO助推器的SBLI点。结果表明，裂纹及其深度对峰值热通量和空气动力相互作用流场具有强烈影响。在浅裂纹（d / C = 0.10）的情况下，裂纹底板上存在两个高热通量区域，它们位于流动的重新附着区域和裂纹的后端壁处。在这种情况下，流重新连接区域的峰值热通量约为停滞点热通量的2倍，与无裂纹TSTO时的峰值热通量相比更大。在深裂纹（d / C = 0.20）的情况下，裂纹底板上的总热通量降低到停滞点热通量以下。％本研究では，二段式宇宙往还机（TSTO：Two-Stage-To-轨道）に対し，裂纹部（机体损伤部，耐热タイル剥落部）において冲撃波•境界层干渉部が起きた场合，裂纹内部の详细な流れ场の解析と空力加热率への影响について调べた。に得られた结果をまとめる。
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