極超音速衝撃波・境界層干渉におけるＣｒａｃｋの空力加熱率への影響

• 小澤 啓伺

  名古屋大学大学院工学研究科航空宇宙工学専攻

• 花井 勝祥

  名古屋大学大学院工学研究科航空宇宙工学専攻

• 北村 圭一

  名古屋大学大学院工学研究科航空宇宙工学専攻

• 森 浩一

  名古屋大学大学院工学研究科航空宇宙工学専攻

• 中村 佳朗

  名古屋大学大学院工学研究科航空宇宙工学専攻

書誌事項

タイトル別名

• Effects of Crack on Heat Flux in Hypersonic Shock/Boundary-Layer Interaction
• キョク チョウオンソク ショウゲキハ キョウカイソウ カンショウ ニ オケル Crack ノ クウリキ カネツリツ エ ノ エイキョウ

抄録

A small crack on body surface led to a tragic accident in 2003, which is the Columbia accident. During the shuttle's re-entry, high temperature gas penetrated crack on leading-edge of the left wing and melted the aluminum structure, finally the Columbia blew up. Since early times, there are many fundamental studies about simple cavity-flow formed on body surface in hypersonic speeds. However, an investigation of Shock/Boundary-Layer Interaction (SBLI) on crack has not been researched. For multistage space transportation vehicle such as TSTO, SBLI is an inevitable problem, and then SBLI on crack becomes a critical issue for TSTO development. 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. These results provide useful data for a development of TSTO thermal protection system (TPS) such as thermal protection tile.

収録刊行物

• 日本航空宇宙学会論文集

  日本航空宇宙学会論文集 58 (674), 68-75, 2010

  一般社団法人 日本航空宇宙学会

キーワード

• Crack
• Heat Flux
• Aerodynamic Interaction
• Hypersonic Flow
• Two-Stage-To-Orbit (TSTO)

詳細情報

• CRID: 1390001204469056640
• NII論文ID: 10026520642
• NII書誌ID: AA11307372
• DOI: 10.2322/jjsass.58.68
• ISSN: 24323691
• ISSN: 13446460
• NDL書誌ID: 10619412
• Web Site: https://ndlsearch.ndl.go.jp/books/R000000004-I10619412
• Web Site: https://www.jstage.jst.go.jp/article/jjsass/58/674/58_674_68/_pdf
• 本文言語コード: ja
• データソース種別:
  • JaLC
  • NDL
  • Crossref
  • CiNii Articles
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