翼型试验阻力测量方法的数值计算研究

分析提出翼型风洞试验时通过翼型尾迹流场信息积分计算阻力的新计算方法,利用数值模拟方法计算多段翼型的流场信息,并以此为基础对传统的尾迹积分计算翼型阻力方法和提出的新方法进行数值比较分析以研究新方法的可行性和准确度.结果表明,在高升力构型(如多段翼型)试验时,相比传统的方法,新提出的方法能得到更准确的阻力值.

Numerical Calculation Research of Measurement Method of Airfoil Drag Test in Wind Tunnel

A new method of drag calculation in Airfoil wind tunnel test by integral calculation of airfoil wake flow field information is presented. Numerical simulation of flow field around multi-element airfoil is finished and with computational information of airfoil wake flow field the airfoil drag is computed by both the traditional drag calculation method and the presented new airfoil drag calculation method. Then two kinds of drag calculation results are compared with the drag results attained by integral computation of surface pressure and shear stress to study the feasibility and accuracy of the presented new method. It is shown from the compare and analyses that for two-dimensional high-lift configuration (such as the multi-element airfoil) wind tunnel test, compared to traditional methods, the pesented new method can attained more accurate drag value.