流れの可視化による2次元超音速ノズル内の流れの実験

抄録

Supersonic flows in two-dimensional nozzle have been investigated numerically by the method of characteristics. In order to confirm the calculated values a visualization study was carried out in the supersonic-flow wind tunnel with the two-dimensional half nozzles. In the cases, the radius of curvature of throat wall/throat width ratio were 4 and 5. The Mach number in the test section of nozzle was taken to be 1. 71. The Mach number of local flow was determined from the Mach angle generated by the wedge-formed tape, the small groove on the center line plate and grains of unvarnished wooden center line surface. The experimental results were in good agreement with the calculated values.