418 遷音速内部流中の二次元対称円弧翼における衝撃波自励振動に与える翼厚の影響(2)(OS4-4 高速流れと衝撃波現象の解明と制御,OS4 高速流れと衝撃波現象の解明と制御,オーガナイズドセッション)

概要

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An experimental study has been carried out to investigate an influence of the airfoil thickness on self-excited shock wave oscillation on a 2D symmetrical circular-arc airfoil in internal transonic flow. 12% and 10% thickness airfoils were tested newly. Shock wave positions were measured by using a line scan camera. The result shows that the shock wave oscillation phenomenon becomes unstable and the continuousness of the shock wave oscillation weakens as the thickness becomes small, and that the shock wave frequency overall lowers as the thickness becomes small, and rises as a shock wave average position gets closer to the trailing edge for the cases of both thicknesses.
一般社団法人日本機械学会の論文
2007-11-17