Study of Boundary Layer Control of Divergent Flow with Shock Wave

概要

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In this paper, it aimed to clarify flow situation in which a supersonic jet, issuing from a divergent nozzle with shock wave, is changed by difference of stagnation pressure and nozzle angle. Angles of the divergent nozzles were 10 degrees and 20 degrees respectively, and the study was done by experiment and numerical analysis. Pressure ratio PdPa was from 1.0 to 6.0 for the experiment, and it was 1.0, 3.0, 6.0, and 10.0 for the numerical analysis. In the experiment., total pressure vibrations and frequency analysis of total pressure vibrations were measured in the vicinity of the nozzle exit. In the numerical analysis, it was examined about velocity contours and pressure contours, Especially, in the experiment., they were confirmed from a result of frequency analysis of total pressure vibrations that the separation point exerted on a jet boundary layer and the flow exerted on self-excited vibration. At the result, according to difference of nozzle's divergent angle and pressure ratio, remarkable differences were seen in the behavior of separation points, the flow behavior of downstream region, and the flow situation in the vicinity of nozzle exit. Moreover, it is clarified in high pressure ratio that flow became a supersonic flow with pseudo-shock wave repeating overexpansion and overcompression.
近畿大学工学部の論文