JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
63333002.pdf1.35 MB
titleJAXA2m×2m遷音速風洞における測定部マッハ数検定試験
Other TitleCalibration of the test section Mach number in the JAXA 2 m x 2 m Transonic Wind Tunnel
Author(jpn)香西 政孝; 上野 真; 塩原 辰郎; 小松 行夫; 唐澤 敏夫; 小池 陽; 須谷 記和; 我那覇 義人; 今 直樹; 原口 智裕
Author(eng)Kozai, Masataka; Ueno, Makoto; Shiohara, Tatsuro; Komatsu, Yukio; Karasawa, Toshio; Koike, Akira; Sudani, Norikazu; Ganaha, Yoshito; Kon, Naoki; Haraguchi, Tomohiro
Author Affiliation(jpn)宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; コスモテック; コスモテック; IHIエアロスペース・エンジニアリング
Author Affiliation(eng)Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Cosmotec Co. Ltd.; Cosmotec Co. Ltd.; IHI Aerospace Engineering Co. Ltd.
Issue Date2007-03-28
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication title第77回風洞研究会議論文集
Proceedings of the Wind Tunnel Technology Association 77th Meeting
Start page6
End page14
Publication date2007-03-28
Languagejpn
AbstractIn the JAXA 2 m x 2 m Transonic Wind Tunnel, there have been more needs of wind tunnel users for high measurement accuracy to develop aircraft and launch vehicles with high performance. To achieve higher accuracy, more elaborate calibration tests to calculate freestream flow conditions have been conducted in this wind tunnel. To obtain test section Mach numbers exactly, test section static pressures must be measured precisely. However, the measurement of test section static pressure is difficult for transonic flows, especially high subsonic flows because of probe nose effects, blockage effects, support interference, and so on. A series of calibration tests is conducted to optimize the static pressure probe for transonic flows and to determine the test section Mach number in the model location from the plenum chamber Mach number.
DescriptionJAXA Special Publication
宇宙航空研究開発機構特別資料
Keywordstransonic wind tunnel; wind tunnel test; Mach number; calibration; static pressure; measuring instrument; accuracy; transonic flow; pressure measurement; 遷音速風洞; 風洞試験; マッハ数; 検定; 静圧; 測定装置; 精度; 遷音速流; 圧力測定
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
SHI-NOAA0063333002
Report NoJAXA-SP-06-026
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/46085


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.