High-speed PIV applied to wake of NASA CRM model at high Re-number sub- and transonic stall conditions
High-speed PIV applied to wake of NASA CRM model at high Re-number sub- and transonic stall conditions
复制标题
高速 PIV 应用于高重数亚音速和跨音速失速条件下 NASA CRM 模型的尾流
DOI：
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发表时间：
2018
期刊：
影响因子：
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通讯作者：
J. Quest
中科院分区：
文献类型：
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作者：
R. Konrath;R. Geisler;J. Agocs;H. Ehlers;Florian Philipp;J. Quest
在欧盟ESWIRP项目的框架内，使用高速相机和激光的粒子图像测速仪(PIV)测量了失速飞机机翼的湍流流动。这些测量是在美国国家航空航天局提供的增压低温欧洲跨音速风洞中提供的普通研究模型上进行的。在风洞设备的低温条件下，已经使用并改装了一种特定的低温PIV系统，以使用高速PIV组件。首次给出了实际雷诺数为1160万和3000万时的跨音速和亚音速失速条件。
Within the framework of the EU project ESWIRP, the particle image velocimetry (PIV) using high-speed camera and laser has been used to measure the turbulent flow in the wake of a stalled aircraft wing. The measurements took place on the common research model provided by NASA in the pressurized cryogenic European Transonic Wind tunnel. A specific cryoPIV system has been used and adapted for using high-speed PIV components under the cryogenic conditions of the wind tunnel facility. First results are presented comprising transonic and subsonic stall conditions at realistic flight Reynolds numbers of 11.6 and 30 million, respectively.