Leeside flows over delta wings at supersonic speeds
Leeside flows over delta wings at supersonic speeds
复制标题
背风以超音速流过三角翼
DOI：
10.2514/3.45014
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发表时间：
1984
期刊：
影响因子：
--
通讯作者：
R. Wood
中科院分区：
文献类型：
--
作者：
David S. Miller;R. Wood
对超音速条件下尖前缘三角翼背风面流动进行了实验研究。压力数据得到数据从1.5到2.8马赫,和三种类型的流动显示数据(简单易行、簇和vapor-screen)得到数据从1.7到2.8马赫的机翼前沿扫描角度52.5度到75度。从流动显示数据,背风面流分为七种不同的类型,他开发了一个图表,将流机制定义为一个函数的条件正常机翼前缘,具体地说,迎角和马赫数。利用实验和半经验预测方法获得的压力数据，研究了攻角、前缘掠度和马赫数对涡强度和涡位置的影响。总的来说，从实验数据中得到的涡致法向力和涡位置的预测值和实测值与迎角、马赫数和前缘后掠角的变化趋势一致；然而，涡诱导的法向力被低估了15%到30%，而涡展向位置被高估了大约15%。
An experimental investigation of the lee-side flow on sharp leading-edge delta wings at supersonic speeds has been conducted. Pressure data were obtained at Mach numbers from 1.5 to 2.8, and three types of flow-visualization data (oil-flow, tuft, and vapor-screen) were obtained at Mach numbers from 1.7 to 2.8 for wing leading-edge sweep angles from 52.5 deg to 75 deg. From the flow-visualization data, the lee-side flows were classified into seven distinct types and a chart was developed that defines the flow mechanism as a function of the conditions normal to the wing leading edge, specifically, angle of attack and Mach number. Pressure data obtained experimentally and by a semiempirical prediction method were employed to investigate the effects of angle of attack, leading-edge sweep, and Mach number on vortex strength and vortex position. In general, the predicted and measured values of vortex-induced normal force and vortex position obtained from experimental data have the same trends with angle of attack, Mach number, and leading-edge sweep; however, the vortex-induced normal force is underpredicted by 15 to 30 percent, and the vortex spanwise location is overpredicted by approximately 15 percent.