楔-后掠柱激波干扰流场和热流的工程算法  

An Engineering Method to Calculate the Interaction Flowfield and Heating on a Wedge- Swept-Cylinder Configuration

作　　者：白菡尘[1] 黄志澄[1] 杨茂昭[1] 朱旗峰 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》1993年第2期224-231,共8页Acta Aerodynamica Sinica

摘　　要：本文针对航天飞机机翼前缘的简化模型,即楔-后掠柱模型,在大后掠、高超声速条件下,提供了一种计算柱体前缘激波干扰流场和热流的工程计算方法。在中国科技大学流体力学实验室的激波风洞中取得了激波干扰的流场显示结果。计算的结果与国内外实验数据的比较表明,这是一种有效的方法。This paper provides an engineering method to calculate shock interaction flowfield and heating rate along the cylinder leading-edge of a wedge-swept-cylinder configuration, which simulated a highly swept wing leading edge of spaccshuttle at hypersonic flow. The interference flowfield schlieren photographs have been obtained in the shock tube of Lab of Fluid Mechanics of the Univercity of Science and Technology of China, The comparison between calculated results and experimental data indicates that this method is more effective than those at home and abroad.

关 键 词：激波干扰 机翼前缘流场 航天飞机 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]