Boundary Layer and Near- Wake Measurements of NACA 0012 Airfoil at Low Reynolds Numbers

机译：低雷诺数的NACA 0012机翼的边界层和近尾测量

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《AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition》|2009年|P.1-12|共12页
会议地点 Orlando FL(US)
作者
D. Kim; J. Yang; J. Chang; J. Chung;
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Korea Aerospace University Goyang Gyeonggi-do South Korea;

Ryerson University Toronto Ontario Canada;

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1. Simulations of High Reynolds Number Air Flow Over the NACA-0012 Airfoil Using the Immersed Boundary Method [J] . James P. Johnson, Gianluca laccarino, Kuo-Huey Chen, Journal of Fluids Engineering: Transactions of the ASME . 2014,第4期

机译：使用浸入边界法模拟NACA-0012机翼上的高雷诺数气流
2. Low Reynolds unsteady flow simulation around NACA0012 airfoil with active flow control [J] . Akbarzadeh P., Lehdarboni A. Askari, Derazgisoo S. M. Meccanica: Journal of the Italian Association of Theoretical and Applied Mechanics . 2018,第14期

机译：NACA0012翼型的低雷诺不稳定流模拟，具有主动流量控制
3. Fluid flow around NACA 0012 airfoil at low-Reynolds numbers with hybrid lattice Boltzmann method [J] . Di Ilio G., Chiappini D., Ubertini S., Computers & Fluids . 2018,第期

机译：用Hybrid格子Boltzmann方法，在低雷诺数周围的Naca 0012翼型的流体流动
4. Boundary Layer and Near- Wake Measurements of NACA 0012 Airfoil at Low Reynolds Numbers [C] . D. Kim, J. Yang, J. Chang, American Institute of Aeronautics and Astronautics Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition . 2009

机译：边界层和NaCA 0012在低雷诺数翼型的近尾瘤测量
5. Study of 3-D Dynamic Roughness Effects on Flow Over a NACA 0012 Airfoil Using Large Eddy Simulations at Low Reynolds Numbers. [D] . Guda, Venkata Subba Sai Satish. 2015

机译：使用低雷诺数下的大型涡流模拟研究3-D动态粗糙度对流经NACA 0012翼型的影响。
6. Boundary Layer Separation and Reattachment Detection on Airfoils by Thermal Flow Sensors [O] . Hannes Sturm, Gerrit Dumstorff, Peter Busche, 2012

机译：热流传感器对机翼的边界层分离和重新附着进行检测
7. Characteristics of the flow over a NACA 0012 airfoil at low Reynolds numbers [O] . R. W. Derksen, M. Agelinchaab, M. Tachie 2014

机译：在低雷诺数下NaCa 0012翼型上的流动特征
8. High Reynolds Number, Low Mach Number, Steady Flow Field Calculations over a NACA 0012 Airfoil Using Navier-Stokes and Interactive Boundary Layer Theory [R] . Cowles, L. J. 1987

机译：利用Navier-stokes和交互边界层理论在NaCa 0012翼型上进行高雷诺数，低马赫数，稳态流场计算

Boundary Layer and Near- Wake Measurements of NACA 0012 Airfoil at Low Reynolds Numbers

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