@inproceedings{oai:jaxa.repo.nii.ac.jp:00005928,
 author = {坂上, 昇史 and 西岡, 通男 and Sakaue, Shoji and Nishioka, Michio},
 book = {宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集　第37回・第38回, JAXA Special Publication: Proceedings of the 37th and 38th JAXA Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Feb},
 note = {To obtain a better understanding of the mechanism for supersonic boundary layer transition, experiments are made at Mach number 2.0 by using a small supersonic wind-tunnel, with focusing efforts on finding non-linear disturbances governing the transition. We examine a boundary layer along the nozzle wall and its transition process by means of quantitative schlieren optical system. It is found that vortical structures our schlieren system visualizes are mostly similar to each other in shape, being stick-like and inclined at about 30 to 70 degrees to the wall, and start to grow often forming a group at streamwise stations where the momentum thickness Reynolds number is around 580 and the transition proceeds as they increase in number to cover the whole boundary layer. We examine the statistical feature of such oblique vortical structures using 1,800 samples and show that these structures are important non-linear disturbances as the mechanism of supersonic boundary layer transition., 資料番号: AA0063156009, レポート番号: JAXA-SP-06-013},
 pages = {27--30},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {超音速境界層の乱流遷移について},
 volume = {JAXA-SP-06-013},
 year = {2007}
}