JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
titlePressure Gradient Effects on Transition Location over Axisymmetric Bodies at Incidence in Supersonic Flow: Progress Report of JAXA-NASA Joint Research Project on Supersonic Boundary Layer Transition Part 2
DOIinfo:doi/10.20637/JAXA-RR-17-003E/0001
Author(jpn)徳川, 直子; 上田, 良稲; 石川, 敬掲; 藤井, 啓介; Choudhari, Meelan; Li, Fei; Chang, ChauLyan; White, Jeffery
Author(eng)Tokugawa, Naoko; Ueda, Yoshine; Ishikawa, Hiroaki; Fujii, Keisuke; Choudhari, Meelan; Li, Fei; Chang, ChauLyan; White, Jeffery
Author Affiliation(jpn)宇宙航空研究開発機構航空技術部門(JAXA); 株式会社トライアングル; ASIRI Inc.; 宇宙航空研究開発機構航空技術部門(JAXA); National Aeronautics and Space Administration (NASA); National Aeronautics and Space Administration (NASA); National Aeronautics and Space Administration (NASA); National Aeronautics and Space Administration (NASA)
Author Affiliation(eng)Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA); TRYANGLE Inc.; ASIRI Inc.; Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA); National Aeronautics and Space Administration (NASA); National Aeronautics and Space Administration (NASA); National Aeronautics and Space Administration (NASA); National Aeronautics and Space Administration (NASA)
Issue Date2017-09-15
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構(JAXA)
Publication titleJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
VolumeJAXA-RR-17-003E
Start page1
End page49
Publication date2017-09-15
Languageeng
AbstractBoundary layer transition along the leeward symmetry plane of axisymmetric bodies at nonzero angle of incidence in supersonic flow was investigated numerically as part of joint research between the Japan Aerospace Exploration Agency (JAXA) and the National Aeronautics and Space Administration (NASA). Stability of the boundary layer over five axisymmetric bodies (namely, the Sears-Haack body, the semi-Sears-Haack body, two straight cones and the flared cone) was analyzed in order to investigate the effects of axial pressure gradients, freestream Mach number and angle of incidence on the boundary layer transition. Moreover, the transition location over four bodies was detected experimentally. The strong effects of axial pressure gradients on the boundary layer profiles along the leeward ray, including an earlier transition under adverse axial pressure gradients, were indicated in both numerical predictions and experimental measurements. The destabilizing effect of the pressure gradient on the boundary layer flow within the leeward symmetry plane is shown to be related to the three-dimensional dynamics involving an increasing build-up of secondary flow along the leeward symmetry plane under an adverse axial pressure gradient. A detailed description of the mean flow computation, which forms the basis for the present linear stability analysis, is provided in an accompanying report that forms part 1 of this document.
DescriptionPhysical characteristics: Original contains color illustrations
形態: カラー図版あり
Keywords3-D Boundary Layer; Transition; Stability Analysis; Experiment
Document TypeTechnical Report
JAXA Category研究開発報告
NASA Subject CategoryAerodynamics
ISSN(online)2433-2216
SHI-NOAA1730005000
Report NoJAXA-RR-17-003E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/774135


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