JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
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Other TitleSurface Pressure Measurement on Axisymmetric Bodies in Supersonic Flow
Author(jpn)徳川, 直子; 赤塚, 純一; 石川, 敬掲; 中北, 和之
Author(eng)Tokugawa, Naoko; Akatsuka, Junichi; Ishikawa, Hiroaki; Nakakita, Kazuyuki
Author Affiliation(jpn)宇宙航空研究開発機構航空プログラムグループ超音速機チーム (JAXA); 宇宙航空研究開発機構研究開発本部風洞技術開発センター計算科学研究グループ; 三向ソフトウェア開発; 宇宙航空研究開発機構研究開発本部風洞技術開発センター計算科学研究グループ
Author Affiliation(eng)Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Wind Tunnel Technology Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Sanko Soft; Wind Tunnel Technology Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Issue Date2012-03-09
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発資料
JAXA research and development memorandum
Start page1
End page21
Publication date2012-03-09
AbstractSurface pressure measurement on axisymmetric bodies in supersonic flow was performed in 1m×1m supersonic wind tunnel in Japan Aerospace Exploration Agency, for the purposes of promoting understanding of transition mechanism, and of validation of computational fluid dynamics, for boundary layers on axisymmetric bodies in supersonic flow. It is confirmed that results of surface pressure measurement by use of conventional pressure tap were in good agreement with numerical results of computational fluid dynamics within the range of the assured measurement precision. Moreover, it is found that the pressure distribution is affected by non-uniformity of freestream in the test section of the wind tunnel, but the influence is negligible small for transition prediction.
DescriptionPhysical characteristics: Original contains color illustrations
形態: カラー図版あり
Keywordspressure measurement; axisymmetric bodies; supersonic flow
Document TypeTechnical Report
JAXA Category研究開発資料
Report NoJAXA-RM-11-016

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