针对自主设计的宽体客机大涵道比涡扇发动机反推格栅，在栅前马赫数Main分别为 0.18、0.30 和 0.35 这3种典型工况下进行了实验与数值模拟研究，获得了反推格栅的气动性能和流场特性，并验证校准了反推格栅的数值模拟方法.数值模拟与实验测量的对比结果表明：数值模拟可以较准确地预测反推格栅的性能；反推格栅的出口总压恢复系数及出口落后角分布均与实验值较为吻合.
In this paper, experimental and numerical simulation methods were employed to investigate the aerodynamic performance and flow field characteristics of an independent design thrust reverser cascade of high bypass ratio turbofan engine for wide-body aircrafts. The numerical simulation was calibrated through experiments at three typical operating points of 0.18, 0.30 and 0.35 inlet Mach number. The results of the comparison between numerical simulation and experimental measurements show that the average total pressure recovery coefficient and the deviation angle of numerical simulation are in good agreement with the experimental results.
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