Anomalous Heating Profile over Entry Capsule with Ablation and Its Relation to Earlier Turbulent Transition
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説明
Effect of earlier turbulent transition and enhancement of turbulence intensity in the boundary layer due to ablation product gas is discussed in terms of anomalous heating profile over the surface of an entry capsule. First, a numerical approach that utilizes Park's injection induced turbulence model is described and some of the numerical results for code validation study are shown. Second, calculated results of trajectory-based aerodynamic heating environment for Pioneer-Venus entry capsules are shown. Finally, a numerical prediction of trajectory-based aerodynamic heating environment for MUSES-C is made and the possible effect of earlier turbulent transition is discussed.
資料番号: SA0200019000
収録刊行物
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- The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
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The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule 17 123-132, 2003-03
宇宙科学研究所
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詳細情報 詳細情報について
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- CRID
- 1050848249892145664
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- NII論文ID
- 120006834551
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- NII書誌ID
- AA10455137
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- ISSN
- 0288433X
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- Web Site
- http://id.nii.ac.jp/1696/00033240/
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- 本文言語コード
- en
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- 資料種別
- departmental bulletin paper
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- データソース種別
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- IRDB
- CiNii Articles