大気吸込式衝撃風洞を使用した翼列流れの圧力計測

抄録

This paper describes a pressure measurement method of the transonic flow through the turbine cascade by means of the suction-type shock tunnel.
The present method which uses silicon oil containing tubes is characterized by an improvement in the response of the pressure-time. It is shown that the values of the static pressures on the blade surfaces measured by the present method almost agree with those by the optical method. The experimental results using a Pitot tube are also shown as an example of this method in order to obtain the total pressures downstream of the cascade.