1990 年 10 巻 1Supplement 号 p. 49-52
The typical flow behaviors within the supersonic air-intake models were visualized by several visualization methods. Here, the results of the oil-flow method for shock-wave/boundary layer interaction flow of the internal channels of the Mach-3 models were presented. Shock-induced saparation, reatachment and foots of the vorticies were visualized. These flow behaviors were affected by strength of shock waves and boundary layer conditions.