Evaluation of Surface Finish Affect on Aerodynamic Coefficients Of Wind Tunnel Testing Models
Evaluation of Surface Finish Affect on Aerodynamic Coefficients Of Wind Tunnel Testing Models
复制标题
表面光洁度对风洞试验模型气动系数影响的评估
DOI：
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发表时间：
2006
期刊：
影响因子：
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通讯作者：
K. Toosi
中科院分区：
文献类型：
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作者：
R. Adelnia;S. Aghanajafi;S. Daneshmand;K. Toosi
在这项研究中，已经进行了确定适用于亚音速和跨音速风洞试验的影响表面粗糙度模型。用于前期研究的几何形状是垂直着陆器概念。垂直着陆器是一个普通的钝圆锥体，后面是一个面包形的底座，底座上表面有两个鳍或整流罩。采用数控加工和磨削的方法，对17-4PH H900钢进行了三种表面粗糙度的加工。每个模型的表面粗糙度平均值（Ra）分别为0.8 µm、1.6 µm和6.3 µm，由光学表面轮廓仪测定。试验的马赫数范围为0.3 ~ 1.2，迎角范围为-4° ~+16°，零侧滑。在每一马赫数下，俯仰力矩、轴向力、法向力和升力与阻力之比的系数都显示出来。研究表明，在马赫数为0.3 ~ 1.2之间，俯仰力矩和法向力的纵向气动力数据在三种模型之间显示出很好的一致性。表面光洁度对轴向力、升阻比等气动特性影响较大。
In this study has been undertaken to determine the suitability of effects surface roughness models for use in subsonic and transonic wind tunnel testing. The geometry used for the precursor study was that of a vertical lander concept. The vertical lander was a generic blunted cone followed by a bread-loaf-shaped base with two fins, or fairings, on the base's upper surface. Three surface roughness were fabricated from Steel 17-4PH H900 by a CNC machining and grinding. The roughness average (Ra) of surfaces for each model was 0.8 µm, 1.6 µm and 6.3 µm that determined by optical surface profilometer. Testing covered the Mach range of Mach 0.3 to Mach 1.2 at an angle-of-attack range of -4° to +16° at zero sideslip. Coefficients of pitching moment, axial force, normal force, and lift over drag are shown at each of these Mach numbers. The study showed that between Mach numbers of 0.3 to 1.2, the longitudinal aerodynamic data in pitching moment and normal force showed very good agreement between the three models. The surface finish does have more effect on the aerodynamic characteristics such as axial force and lift over drag.