| タイトル | Computational Investigation of Supersonic Boundary Layer Transition Over Canonical Fuselage Nose Configurations |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120012434 |
| 著者（英） | Li, Fei; Atobe, Takashi; Ishikawa, Hiroaki; Chang, Chau-Lyan; Tokugawa, Naoko; White, Jeffery A.; Choudhari, Meelan M.; Ueda, Yoshine; Fujii, Keisuke |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2012-07-09 |
| 言語 | eng |
| 内容記述 | Boundary layer transition over axisymmetric bodies at non-zero angle of attack in supersonic flow is numerically investigated as part of joint research between the National Aeronautics and Space Administration (NASA) and Japan Aerospace Exploration Agency (JAXA). Transition over four axisymmetric bodies (namely, Sears-Haack body, semi-Sears-Haack body, 5-degree straight cone and flared cone) with different axial pressure gradients has been studied at Mach 2 in order to understand the effect of axial pressure gradient on instability amplification along the leeward symmetry plane and in the region of nonzero crossflow away from it. Comparisons are made with measured transition data in Mach 2 facilities as well as with predicted and measured transition characteristics for a 5-degree straight cone in a Mach 3.5 low disturbance tunnel. Limitations of using linear stability correlations for predicting transition over axisymmetric bodies at angle of attack are pointed out. |
| NASA分類 | Aerodynamics |
| レポートNO | NF1676L-13982 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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