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利用自主软件NAPA对典型带输出轴的直升机进气道进行了三维流场数值分析,通过修正进气道输出轴迎风侧的管道曲率半径、在背风侧增添优化的尾锥,改进设计了原型进气道并进行了模拟.结果表明,原型进气道由于输出轴堵塞了流道,使输出轴背风侧存在很大的分离,同时迎风侧存在转弯损失,导致出口面流场畸变严重.改型进气道减小了输出轴背风侧的分离和迎风侧的转弯损失,使其既保持了高总压恢复系数,且畸变指数最大降低了74%.
The NAPA software was used to analyze the typical three-dimensional flow field of a typical helicopter inlet with an output shaft. By modifying the curvature radius of the pipe on the windward side of the inlet shaft and adding an optimized tail cone on the leeward side, the prototype was improved The results show that the inlet of the prototype has blockage of the flow passage due to the output shaft, which results in a large separation of the leeward side of the output shaft and the turning loss on the windward side, resulting in serious distortion of the flow field at the outlet. The inlet reduces the separation of the leeward side of the output shaft and the turning loss on the windward side, so that the high total pressure recovery coefficient is maintained and the maximum distortion index is reduced by 74%.