ロケット用超音速ノズルの形状が過膨張時の流れのはく離に及ぼす影響(流体工学,流体機械)

概要

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In the present paper, parametric numerical analyses of the separated transonic flows in overexpanded rocket nozzles are conducted. Several types of nozzles are examined numerically to clarify the detailed mechanisms of the occurrence of restricted shock separation (RSS) in the compressed truncated perfect (CTP) nozzle. The parameter of the nozzle contour examined is its length and compression factor. In the CTP nozzle with large length and small compression factor, a positive pressure gradient is formed downstream of the Mach disk before the occurrence of RSS. Under the positive pressure gradient, the flow which passed through the Mach disk rolls up and forms a large vortex ring around the central axis of the nozzle. The vortex ring pushes the separated jet to the nozzle wall and results in RSS.
一般社団法人日本機械学会の論文
2005-07-25