308 2次元不始動超音速翼列の失速線近傍における数値計算(OS-7 翼・翼列)

概要

論文の詳細を見る
Numerical analyses were carried out to understand the unsteady characteristics of unstarted flow near the stall line in a two-dimensional supersonic cascade. The result shows that detached shock on the blade suction side moves upstream to the blade leading edge of the preceding blade as we increase the pressure ratio. The accelerated region upstream of the shock becomes smaller as the shock moves upstream. The shock disappears when it reaches the leading edge on the suction side because the flow upstream of the shock is not sufficiently accelerated. The disappeared shock will not recover because leading edge suction is weakened by separation which was behind the shock. These phenomena are considered to be the inception of full stall in unstarted flow.
一般社団法人日本機械学会の論文
2000-03-16