相对弯度对钝尾缘改型提升翼型气动性能的影响

发布时间：2018-03-18 05:22

本文选题：风力机　切入点：相对弯度　出处：《农业机械学报》2014年08期 　论文类型：期刊论文

【摘要】：研究不同弯度的风力机专用翼型修改前后的气动性能,揭示相对弯度对钝尾缘改型增升效果的影响规律。利用XFOIL软件,对低速翼型S809、S823和S830进行尾缘厚度对称分布的钝尾缘改型。采用S-A和k-ωSST湍流模型模拟翼型原型的气动性能,并用实验数据比较两模型的计算精度。进而基于精度较高的k-ωSST湍流模型,计算了修改后翼型的升、阻力系数、升阻比和三者增幅,以及翼型表面压力系数分布。结果表明:对低速翼型进行钝尾缘改型时,随相对弯度增大,升力系数增幅在一定攻角范围内先增大后减小,升阻比增幅在一定攻角之前呈递增趋势;相对弯度约为2.5%弦长的翼型增升效果最佳,且大弯度翼型不适合钝尾缘改型。
[Abstract]:The wind turbine airfoil of different curvature before and after modification of aerodynamic performance, to reveal the effects of increasing rise of relative camber effect of blunt trailing edge modification. By using the software of XFOIL, S823 and S809 on low speed airfoils, S830 thickness of trailing edge symmetrical blunt trailing edge modification. The aerodynamic performance by S-A and k-. The SST turbulence model simulation of airfoil prototype of the gas, and the calculation precision with the experiment data comparison of two models. Then Omega k- SST turbulence model with high accuracy based on the rise, the modified airfoil to calculate the drag coefficient, lift drag ratio and an increase of three, and the pressure distribution on the airfoil surface coefficient. The results showed that: blunt trailing edge modification on low speed with the increase of relative camber airfoil, and increase the lift coefficient first increases under certain angle of attack range decreased, the lift drag ratio increase at a certain angle of attack before increasing trend; the relative camber is about 2.5% chord airfoil lift and best effect. Cambered airfoil is not suitable for blunt trailing edge modification.

【作者单位】：天津工业大学天津市现代机电装备技术重点实验室;天津城建大学能源与安全工程学院;
【基金】：天津市自然科学基金青年资助项目(13JCQNJC07000) 天津市高等学校科技发展基金资助项目(20130425) 国家自然科学基金资助项目(11102134)
【分类号】：TM315

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