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翼型风洞试验阻力测量常使用尾迹流场测量积分求取阻力的方法,但各积分公式均建立在一定的假设基础上,有一定适用范围。在多段翼型流场N-S方程数值模拟和风洞试验的基础上,研究高升力情况下低速风洞阻力精确测量技术。通过N-S方程数值模拟求解多段翼型绕流场,分析尾迹流场的特点和常规风洞试验阻力计算公式推导时所作假设,提出新的更为准确的型阻计算公式;利用多段翼型绕流的数值模拟结果,积分表面压力和摩擦力求得翼型的气动特性,并利用计算得到的尾迹流场信息按照常规和新提出的风洞试验型阻计算公式计算阻力,将三者进行比较,检验提出的新型阻计算公式的准确性;通过风洞试验检验数值模拟得到的流场特点和新型阻计算公式。研究表明:在高升力条件下,传统型阻计算公式有很大的局限性,必须进行改进;提出的考虑尾迹区流动特点的新型阻计算公式能够得到更准确的阻力值。
Airfoil Wind Tunnel Test Resistance measurement often uses the wake flow field measurement integral method to obtain resistance, but the integral formula are based on certain assumptions, have a certain scope of application. Based on numerical simulation of N-S equation and wind tunnel test of multi-section airfoil, the accurate measurement technology of low-speed wind tunnel resistance under high-lift condition is studied. Navier-Stokes numerical simulation is used to solve the multi-section airfoil around the flow field, the characteristics of the wake flow field and the assumptions made in the calculation formula of conventional wind tunnel test resistance are analyzed, and a new and more accurate model calculation formula is proposed. The aerodynamic characteristics of the airfoil are obtained by integrating the surface pressure and the friction force. The calculated resistance of the airfoil is calculated according to the flow field information of the wake obtained by the conventional and new wind tunnel test. The three are compared and tested The accuracy of the proposed new resistance calculation formula is verified. The characteristics of the flow field and the new resistance calculation formula obtained by numerical simulation are verified by wind tunnel test. The research shows that under high lift conditions, the traditional formula for calculating the resistance has great limitations and must be improved. The proposed new formula for calculating the resistance considering the wake characteristics can obtain more accurate resistance values.