超音速風洞ノズルの形状最適化 : 第2報,実機ノズル最適化への適用(流体工学,流体機械)

概要

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The optimization procedure of the supersonic wind tunnel nozzle geometry is verified in the National Aerospace Laboratory (NAL) 1m×1m supersonic wind tunnel. The procedure is carried out by a slight displacement in each jack of the variable nozzle from the initial position. Mach number distribution was obtained by measuring total pressure in the measuring region with a pitot rake. Mach number 2.1, 2.2, 2.3, 2.5, 3.0, 3.5, and 4.0 nozzle contours were optimized in this procedure, and Mach number deviation in the measuring region was reduced below 1.0% of mean Mach number in each nozzle contour.
社団法人日本機械学会の論文
2003-04-25