JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
62081000.pdf18.1 MB
titleExperimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project (Part 2)
Author(jpn)吉田, 憲司; 上田, 良稲; Vermeersch, Olivier; Arnal, Daniel
Author(eng)Yoshida, Kenji; Ueda, Yoshine; Vermeersch, Olivier; Arnal, Daniel
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; 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; フランス航空宇宙研究所空力/エネルギーモデル部; フランス航空宇宙研究所空力/エネルギーモデル部
Author Affiliation(eng)Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Department of Modeling for Aerodynamics and Energetics (DMAE), ONERA; Department of Modeling for Aerodynamics and Energetics (DMAE), ONERA
Issue Date2013-03-29
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発報告
JAXA research and development report
VolumeJAXA-RR-12-009E
Start page1
End page142
Publication date2013-03-29
Languageeng
AbstractStability 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.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
Keywordsboundary layer transition; supersonic fl ow; linear stability analysis; e(N) method; natural laminar flow wing; flight test; wind tunnel test
Document TypeTechnical Report
JAXA Category研究開発報告
NASA Subject CategoryAerodynamics
ISSN1349-1113
NCIDAA1192675X
SHI-NOAA0062081000
Report NoJAXA-RR-12-009E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/18524


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