收敛扩散喷管超音速喷射噪声和前向飞行效应

2011/02/24   下载量： 8 次

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应用领域 其他
检测样本 其他
检测项目
参考标准 暂无

Flow and far-field noise measurements are taken on a conical Convergent- Divergent nozzle similar to the nozzles employed on high-performance tactical jets. Matching flow and far-field computations are presented, produced by Large Eddy Simulation and the Kirchhoff integral method. The conditions examined are those in which the nozzle is operated at its design Mach number of 1.56 while forward flight is simulated at Mach numbers of 0.1, 0.3 and 0.8. Both measurement and LES show that increasing forward flight Mach number to the high subsonic range shortens the initial shock cell size, and weakens the shock cells induced by the nozzle throat relative to the shock cells induced by the nozzle lip. LES shows that high forward flight speed substantially reduces the noise radiated into the forward quadrant where shock noise is dominant. It also removes the screech tone entirely.

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北京欧兰科技发展有限公司
金牌会员 丨 第17年
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