AM05-04-008 超音速境界層遷移を支配する非線形撹乱に関する実験的研究(境界層とせん断流2,一般講演)

概要

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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 1800 samples and show that these structures are important non-linear disturbances as the mechanism of supersonic boundary layer transition.
日本流体力学会の論文
2005-09-05