書誌事項
- タイトル別名
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- S1910103 Computation of Forced Turbulent Flow over Reentry Capsule Afterbody with High Order Scheme
抄録
An aeroheating measurement test campaign on an Apollo capsule model with turbulent boundary layers was performed in the free-piston shock tunnel HIEST at JAXA Kakuda Space Center. When flow became turbulent flow, heat flux on fore and rear body was 1.5-2 times larger than one in laminar flow. In order to reproduce the heat flux by numerical simulation, we constructed high order CFD code towards LES in hypersonic flow. Since robustness near shock and high resolution in boundary layer is needed for LES in hypersonic flow, we employed recently improved WENO method. We calculated the hypersonic flow (M_∞ = 17) around cylinder and investigated the robustness for strong shock by this method. We could obtain smooth pressure distribution and good agreement with the calculated heat flux by NASA LAURA code. The hypersonic flow field around HTV-R, which is a manned space capsule under development by JAXA was also calculated towards predicting heat flux on after body.
収録刊行物
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- 年次大会
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年次大会 2014 (0), _S1910103--_S1910103-, 2014
一般社団法人 日本機械学会
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詳細情報 詳細情報について
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- CRID
- 1390001205843547264
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- NII論文ID
- 110009945374
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- ISSN
- 24242667
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可