超音速低乱ノズルの設計と実験による検証 [in Japanese] Design and Experimental Evaluation of Supersonic Quiet Nozzles [in Japanese]
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A Mach 3.6 axisymmetric nozzle is designed based on the transition predictions of the nozzle wall boundary layers using the linear stability analysis of Gortler vortices with the e<SUP>N</SUP> method. The experimental results of flow quality measurements and boundary layer transition data on a cone in the designed noxzle over a unit Reynolds number range of 4.3-5.9×10<SUP>7</SUP>/m are presented. The measured transition Reynolds numbers on the cone increase as the wall temperature of the cone decreases. The maximum Reynolds number of 7.7×10<SUP>6</SUP>/m obtained in the experiment is close to the theoretical predictions of linear stability tkeory. The effects of surface finish of the nozzle wall on the flow qualities and the transition Reynolds numbers on the cone were also observed.
- JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 47(549), 367-373, 1999-10
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES