超音速流における乱流境界層遷移制御

抄録

The purpose of this study is to compare predictions based on conservation law models with experimental results and to control the boundary layer transition by changing the bluntness of the leading edge of the flat plate. In the experiment, the transition was measured from thermocouple temperature measurements in a high-speed wind tunnel at Mach 2. The bluntness promoted a delay in the transition. As a result, the transition positions were backward to a smaller range than predicted by Newtonian flow theory. In addition, the larger bluntness, the larger transition Reynolds number.