| 翼型改型对超临界翼型气动性能影响的数值研究 |
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| 引用本文： | 陆超,徐志晖,张广.翼型改型对超临界翼型气动性能影响的数值研究[J].沈阳航空工业学院学报,2008,25(5). |
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| 作者姓名： | 陆超 徐志晖 张广 |
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| 作者单位： | 沈阳航空工业学院动力与能源工程学院,辽宁,沈阳,110136 |
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| 摘 要： | 为了深入研究改型对跨声速翼型气动性能的影响,对NASA SC(2)-0614翼型进行多种方案的改型,包括前缘半径、厚度、弯度、翼型上表面形状等,并得出最终优化改型方案.数值模拟结果表明,改型后翼型设计状态下升阻比和临界马赫数均有显著提高.
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| 关 键 词： | 超临界翼型 临界马赫数 升阻比 |
Effect numerical study of modified airfoil on aerodynamic performance of supercritical airfoil |
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| LU Chao,XU Zhi-hui,ZHANG Guang.Effect numerical study of modified airfoil on aerodynamic performance of supercritical airfoil[J].Journal of Shenyang Institute of Aeronautical Engineering,2008,25(5). |
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| Authors: | LU Chao XU Zhi-hui ZHANG Guang |
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| Institution: | Aircraft Power and Engineering College;Shenyang Institute of Aeronautical Engineering;Liaoning Shenyang 110136 |
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| Abstract: | This paper investigated the effect of several modifications of NASA SC(2)-0614 airfoil,including leading edge radius,thickness,curvature and suction surface of the airfoil,etc.,including its aerodynamic performance and final modified airfoil optimization.The numerical simulation show that the lift drag coefficient and critical March number has increased significantly for the modified airfoil at the design point. |
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| Keywords: | supercritical airfoil critical march number lift drag coefficient |
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