摘要
基于正交试验的方法,采用XFOIL软件研究最大相对厚度、最大相对弯度以及尾缘厚度对翼型前缘粗糙度敏感性的影响,推导评价翼型粗糙度敏感性的指标,并讨论翼型表面不同区域加密面元节点对XFOIL软件计算结果的影响。研究表明,在翼型上表面正压力梯度区域加密面元节点会对XFOIL软件的计算结果产生明显的影响,而在其它区域增加面元节点个数会增加计算的收敛速度,但对计算结果没有明显的影响。通过极差和方差分析发现,翼型前缘粗糙会导致翼型多方面的气动性能参数变坏,翼型的最大相对厚度会对所有的敏感性指标产生显著性影响,而最大相对弯度和尾缘厚度仅对其中一些指标产生明显的影响,且增大翼型的尾缘厚度有利于降低由于前缘粗糙引起的升力系数和升阻比的下降。
Based on the method of orthogonal test, researches the influence that the maximum relative thickness, the maxim relative camber and trailing edge thickness of airfoil exert upon the airfoil leading edge roughness sensitivity, to evaluate the airfoil roughness sensitivity index, and discusses the effect that increasing surface plane node on different regions of airfoil surface exerts upon the calculation results of the XFOIL software. The results show that inserting the surface node on the negative normal pressure gradient region of upper surface has a significant effect on the calculation results, and on the other rest of region of airfoil, the speed of convergence will increase, but no obvious effect on the calculation results. Through range and variance analysis, it was found that the roughness in the leading edge of airfoil will result in the deterioration of aerodynamic performance, and the maximum relative thickness in airfoil will have a significant impact on all the indictors of the sensitivity of airfoil, but the maximum relative camber and the trailing edge thickness only on some indicators among them. Meanwhile the increase of trailing edge thickness will positively exert upon cutting down the decrease of the lift coefficient and lift-drag ratio caused by the leading edge roughness of airfoil.
出处
《机械工程学报》
EI
CAS
CSCD
北大核心
2018年第14期198-206,共9页
Journal of Mechanical Engineering
基金
长江学者和创新团队发展计划资助项目(IRT13052)
