等离子体热效应对NACA0012翼型增升减阻的研究

doi:10.13675/j.cnki.tjjs.190574

推进技术 ›› 2020, Vol. 41 ›› Issue (5): 1055-1062.DOI: 10.13675/j.cnki.tjjs.190574

等离子体热效应对NACA0012翼型增升减阻的研究

刘加伟¹，柳兆涛¹，丁仕洪²，姚程^1,3

1.合肥工业大学土木与水利工程学院，安徽合肥 230009;2.中铁四局集团钢结构有限公司，安徽合肥 230022;3.合肥工业大学土木工程结构与材料安徽省重点实验室，安徽合肥 230009

发布日期:2021-08-15
作者简介:刘加伟，硕士生，研究领域为等离子体流动控制。E-mail：369171859@qq.com
基金资助:
国家自然科学基金（51906054）；中央高校基本科研业务费专项资金（PA2019GDPK0038）。

Study on Lift Enhancement and Drag Reduction of NACA0012Airfoil under Plasma Thermal Effect

1.School of Civil and Hydraulic Engineering,Hefei University of Technology,Hefei 230009,China;2.Steel Structure Construction,LTD of China Tiesiju Civil Engineering Group,Hefei 230022,China;3.Anhui Key Laboratory of Civil Engineering Structures and Materials,Hefei University of Technology,Hefei 230009,China

Published:2021-08-15

摘要/Abstract

摘要： 基于等离子体热效应机理，在来流速度为34m/s和攻角0~12°内，对NACA0012翼型在等离子体激励下的流场特性进行数值模拟。通过研究等离子体激励的位置和数量对翼型的升阻力特性的影响，得出翼型增升减阻的最佳位置和数量。为保证计算模型的准确性，将未激励的翼型流场参数与NASA实验数据进行对比验证。结果表明：未激励翼型的流场计算参数与实验结果吻合度较高；在等离子体单激励下，最佳减阻位置位于翼型下表面的前缘，最佳增升位置位于翼型下表面的后缘，且二者受攻角的影响较大；在翼型下表面的前缘和后缘同时施加激励时，翼型的减阻比约为20%，最大增升比为52%。

关键词: 热效应;激励位置;激励数量;流场参数;增升;减阻

Abstract: Based on the mechanism of plasma thermal effect, the flow field characteristics of NACA0012 airfoil under plasma excitation were numerically simulated when the incoming flow velocity was 34m/s and the angle of attack was within 0~12°. The effects of the position and number of plasma excitation on the airfoil’s lift and drag characteristics were studied to obtain the optimum position and quantity for increasing lift and reducing drag of the airfoil. To ensure the accuracy of the computational model, the unexcited airfoil flow field calculation parameters were compared with NASA experimental data for verification. The results show that: the flow field calculation parameters of the unexcited airfoil are in good agreement with the experimental results. Under single plasma excitation, the optimal drag reduction position is located at the leading edge of the airfoil’s lower surface and the optimal lift enhancement position is located at the trailing edge of the airfoil’s lower surface, and both are greatly affected by the angle of attack. When the leading edge and the trailing edge of the airfoil’s lower surface are excited simultaneously, the drag reduction ratio of airfoil is about 20% and the maximum lift enhancement ratio is 52%.

Key words: Thermal effect;Excitation position;Number of excitation;Flow field parameters;Lift enhancement;Drag reduction

刘加伟，柳兆涛，丁仕洪，姚程. 等离子体热效应对NACA0012翼型增升减阻的研究[J]. 推进技术, 2020, 41(5): 1055-1062.

LIU Jia-wei¹, LIU Zhao-tao¹, DING Shi-hong², YAO Cheng^1,3. Study on Lift Enhancement and Drag Reduction of NACA0012Airfoil under Plasma Thermal Effect[J]. Journal of Propulsion Technology, 2020, 41(5): 1055-1062.

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等离子体热效应对NACA0012翼型增升减阻的研究

Study on Lift Enhancement and Drag Reduction of NACA0012Airfoil under Plasma Thermal Effect

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