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Inlet Vortex Generator Design for the X-59 Low Boom Flight Demonstrator

机译：入口涡流发生器设计X-59低繁荣飞行演示

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An array of vortex generators was designed for the X-59 Low Boom Flight Demonstrator aircraft inlet. Prior to a High Speed Inlet Distortion Test, concern regarding potentially high measurements of steady state or dynamic distortion prompted an effort to examine the use of passive flow control to reduce distortion levels. Design of experiments methodology was used to develop two matrices of vortex generators placed inside the inlet serpentine duct and upstream of the inlet on the compression surface, varying on several geometric parameters. Reynolds-Averaged Navier-Stokes simulations were performed using the FUN3D flow solver at Mach 1.45 to analyze the impact of each configuration on total pressure recovery, circumferential distortion, and radial distortion. Results from simulations of the baseline aircraft are compared with data acquired in the NASA Glenn Research Center's 8- by 6-foot Supersonic Wind Tunnel. A vortex generator configuration with vanes placed upstream of the inlet terminal shock was shown to significantly increase total pressure recovery and decrease circumferential distortion with no penalty to radial distortion levels. Inlet mass flow sweeps at Mach 1.45, 0.6, and 0.3 indicated no detrimental effects from the vanes at off-design conditions.
机译：设计了一系列涡流发电机，专为X-59低繁荣飞行演示航空器入口。在高速入口失真测试之前，关于稳定状态或动态失真的潜在高测量的关注促使努力检查使用被动流量控制以减少失真水平。实验方法的设计方法用于开发两个涡流发生器的矩阵放置在入口蛇形管道内部和压缩表面上的入口上游，在几个几何参数上变化。使用Mach 1.45的Fun3D流动求解器进行雷诺瓦斯平均血管模拟，以分析每个配置对总压力恢复，周向失真和径向失真的影响。基线飞机的模拟结果与NASA Glenn Research Center 8-乘6英尺超声波风洞所获取的数据进行比较。涡旋发生器配置具有放置在入口端子冲击的上游的叶片，显着增加了总压力恢复，并减少了径向失真水平的圆周变形。在Mach 1.45,0.6和0.3的入口质量流动扫描表明在非设计条件下没有叶片的不利影响。

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