Shock Tube as a Device for Testing Transonic Airfoils at High Reynolds Numbers
Shock Tube as a Device for Testing Transonic Airfoils at High Reynolds Numbers
复制标题
激波管作为高雷诺数测试跨音速翼型的装置
DOI：
10.2514/3.61208
复制
发表时间：
1979
期刊：
影响因子：
2.5
通讯作者：
G. Chapman
中科院分区：
文献类型：
--
作者：
W. Cook;L. Presley;G. Chapman
气动激波管的性能分析表明，大型激波管在主激波后可以产生弦雷诺数在1亿范围内的跨声速翼型流动。在低雷诺数和中雷诺数条件下对简单翼型的流动进行了研究，以评估测试技术。从纹影照片和翼型压力测量得到的结果表明，在可用的测试时间内，在具有适当轮廓的测试截面壁面或设计适当的开槽壁面的激波管内，可以产生与在风洞中观察到的翼型相似的稳定跨音速流动。研究表明，激波管是研究二维高雷诺数跨音速翼型流动的有效工具。
A performance analysis of gas-driven shock tubes shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be generated behind the primary shock in a large shock tube. A study of flow over simple airfoils has been carried out at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photos and airfoil pressure measurements show that steady transonic flows similar to those observed for the airfoils in wind tunnels can be generated within the available testing time in a shock tube with either properly-contoured test section walls or a properly-designed slotted-wall test section. The study indicates that the shock tube is a useful facility for studying two-dimensional high Reynolds number transonic airfoil flows.