Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project (Part 2)

Material type: 文書・図像類

Author: 吉田, 憲司ほか

Publisher: 宇宙航空研究開発機構(JAXA)

Publication date: 2013-03-29

Material Format: Digital

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Note (General)：: Stability analysis on a supersonic natural laminar flow (NLF) wing designed by JAXA was performed at both flight and wind tunnel test conditions as a ...

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Material Type: 文書・図像類
Title: Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project (Part 2)
Author/Editor: 吉田, 憲司
上田, 良稲
Vermeersch, Olivier
Arnal, Daniel
Yoshida, Kenji
Ueda, Yoshine
Author Heading: 吉田, 憲司
上田, 良稲
Vermeersch, Olivier
Arnal, Daniel
Yoshida, Kenji
Ueda, Yoshine
Publication, Distribution, etc.: 宇宙航空研究開発機構(JAXA)
Publication Date: 2013-03-29
Publication Date (W3CDTF): 2013-03-29
Periodical title: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report
No. or year of volume/issue: JAXA-RR-12-009E
Volume: JAXA-RR-12-009E
Pages: 1-142
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: eng
Subject Heading: boundary layer transition
supersonic fl ow
linear stability analysis
e(N) method
natural laminar flow wing
flight test
wind tunnel test
Target Audience: 一般
Note (General): Stability analysis on a supersonic natural laminar flow (NLF) wing designed by JAXA was performed at both flight and wind tunnel test conditions as a joint research program between ONERA and JAXA. Both parties validated the NLF wing effect by confirming suppression of crossflow instability at design point, using an e(N) method with fixed β strategy proposed by ONERA. Although JAXA’s flight test vehicle and wind tunnel test model had almost same averaged roughness height of about 1micrometer, it was shown that surface roughness had little influence on measured transition location at both flight and wind tunnel test conditions. Furthermore, JAXA found that the pressure distribution measured in flight test did not completely coincide to the target pressure distribution (Cp (Target)) for the NLF wing design. It revealed that measured transition location at outer wing region was not delayed in flight test, compared with the transition location predicted with the Cp (Target) which had large gain to delay the transition. Influence of Reynolds number on transition location was also studied for the target pressure distribution Cp (Target). Consequently, chordwise transition location, (x/c)Tr., rapidly moves from mid-chord location to forward location (near leading edge) for increasing Reynolds numbers, according to the change of instability of boundary layer from Tollmien-Schlichting instability to crossflow instability.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA0062081000
レポート番号: JAXA-RR-12-009E
Access Restrictions: 限定公開
Periodical Title (NCID): AA1192675X
https://ci.nii.ac.jp/ncid/AA1192675X
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ