Abstract
This paper describes the application of the optimization procedure for a supersonic wind tunnel two-dimensional variable nozzle contour developed in the previous report to the optimization of a hypersonic wind tunnel axisymmetric nozzle contour of Mach number higher than 5.0. In this procedure, several positions are set on the nozzle wall, and using the linearity of a displacement of each position to the flow pattern, the optimum nozzle contour is determined in a few cases of CFD analyses. To take an axisymmetric nozzle of Mach number 10.0 as an example, optimization was carried out. Mach number deviation in the uniform flow region reduced from 1.48% to 0.40% by the optimization.
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