A 10%-scale high-lift version of the Common Research Model (CRM-HL) was tested in the NASA Langley Research Center’s 14 by 22 ft subsonic tunnel. The focus of the wind-tunnel tests was to investigate the vortices generated at the nacelle/pylon region and their effect on the aerodynamic performance. The wind-tunnel measurements included the acquisition of force and moment data, steady pressure data, as well as surface flow visualization using minitufts. For some select cases, numerical simulations were performed to aid in understanding the wind-tunnel data. Wind-tunnel tests, with and without the nacelle/pylon, indicated a lift degradation of the conventional CRM-HL at high angles of attack. The surface flow visualization with fluorescent minitufts revealed that the lift degradation is due to flow separation caused by the nacelle/pylon vortex system on the inboard wing. The consequent flow separation was successfully mitigated using a nacelle chine installed on the inboard side of the engine nacelle.

在NASA兰利研究中心的14英尺高22英尺亚音速隧道中测试了10％比例高升程的通用研究模型（CRM-HL）。风洞测试的重点是研究在机舱/塔架区域产生的涡流及其对空气动力性能的影响。风洞测量包括力和力矩数据，稳定压力数据的采集，以及使用微型簇的表面流可视化。对于某些特定情况，进行了数值模拟，以帮助理解风洞数据。带有和不带有机舱/吊架的风洞测试表明，传统的CRM-HL在大迎角下的升力下降。具有荧光微型簇的表面流可视化显示，升力下降是由于内侧机翼上的机舱/塔架涡流系统引起的流分离所致。使用安装在发动机机舱内侧的机舱内齿圈成功缓解了由此造成的气流分离。