10度円錐体に発達する超音速境界層遷移の可視化に関する研究(流体工学,流体機械)

抄録

A boundary layer transition on a 10-degree cone model in a supersonic flow was visualized by means of a temperature-sensitive paint (TSP). A transition front can be detected as the edge of brightness measuring the temperature difference between laminar and turbulent boundary layers. To enhance a thermal signature across the transition line, a sudden temperature step is introduced into the wind tunnel and global transition patterns on the cone model were clearly visualized. In this study, a quiet test region in the test section was visualized first. Then, the effects of Mach numbers, Reynolds numbers and angles of attack on the transition patterns were studied with emphasis on transition caused by crossflow instability.