@inproceedings{oai:jaxa.repo.nii.ac.jp:00005653,
 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39回, JAXA Special Publication: Proceedings of the 39th JAXA Workshops on Investigation and Control of Boundary-Layer Transition},
 month = {Dec},
 note = {This numerical study examines the supersonic rectangular-nozzle flow by focusing attention on the development of secondary flow and corner-flow and their effects on the boundary layer instability and transition. The results show that secondary flows appear in the side wall boundary layers and form into streamwise vortices in the corner region immediately behind the throat station where the boundary layer momentum thickness Reynolds number is 400. The streamwise vortex increases in number downstream and induces a local normal-to-wall flow as large as 4 percent of the local mainstream. The present simulation is in good agreement with the corresponding experiment, in particular, on the appearance of cross-flow instability on the side wall boundary layer and the streamwise location where the streamwise vortex first appears. The corner-flow is found to be of extremely unstable nature suggesting that the turbulent transition observed is directly caused by the corner-flow disturbances., 資料番号: AA0063608008, レポート番号: JAXA-SP-07-009},
 pages = {23--26},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {矩形超音速ノズル境界層の不安定性について},
 volume = {JAXA-SP-07-009},
 year = {2007}
}