油膜干涉测量翼型壁面摩阻低速风洞试验技术 |
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引用本文: | 耿子海,史志伟,金启刚.油膜干涉测量翼型壁面摩阻低速风洞试验技术[J].空气动力学学报,2016(1):80-85. |
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作者姓名: | 耿子海 史志伟 金启刚 |
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作者单位: | 1. 西北工业大学,陕西 西安,710072; 中国空气动力研究与发展中心,四川 绵阳 621000;2. 南京航空航天大学,江苏 南京,210016;3. 中国空气动力研究与发展中心,四川 绵阳,621000 |
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摘 要: | 油膜干涉试验可以定量测量得到模型壁面的摩擦应力,是开展摩阻特性研究的有力工具。通过对油膜干涉试验技术中的试验原理、试验方法、误差修正、数据结果分析等关键问题的研究,初步建立了试验系统,具备了开展模型壁面摩阻特性研究的试验能力。综合分析表面热膜试验结果与数值计算结果,在以模型弦长为特征长度,试验雷诺数 Re =1.3×106的条件下,翼型表面摩擦应力沿模型弦向的分布规律具有较好的一致性。
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关 键 词: | 油膜干涉试验 定量测量 壁面摩擦应力 数值计算 |
Invetigation of skin-friction measurements using oil-film interferometry on airfoil wall in low speed wind tunnel |
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Abstract: | Oil-film interferometry is a possible technique for skin friction measurement quan-titatively in a wind tunnel.Test principles,test methods,error correction,data analysis and some other related key issues of oil-film interferometry technique are investigated.A primary test system is established to measure skin-frictions of two laminar flow airfoils in a low speed wind tunnel.Error correction for high quality skin-friction measurements is also developed .Both lam-inar and turbulent skin friction are successfully obtained.Furthermore,skin-frictions are also calculated numerically.The results between tests and numerical calculation of chordwise skin friction distribution for two laminar airfoils shown good agreement. |
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Keywords: | oil-film interferometry test quantitative measurement skin-friction numerical calculation |
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