民机高速风洞试验的阻力雷诺数效应修正

Drag's Reynolds Number Effect Correction of High Speed Wind Tunnel Test for Civil Aircraft

在飞机设计阶段,获得准确的气动特性数据对设计者是十分重要的,采用缩比模型的风洞试验是主要途径之一。但是风洞条件限制了试验的Re数,从而影响了对跨音速巡航阻力的评估,因此需要对风洞试验结果的阻力进行Re数效应修正。分析了风洞试验结果阻力的误差构成,提出了Re数效应修正的风洞试验数据基础;进一步就跨音速巡航阻力的构成进行分析,论述了对最小阻力和升致阻力分项修正的方法,并对修正结果进行了验证,得到了一种可靠的工程方法。

It is important to get the accuracy aerodynamic character data for designers during the airplane design phase. The wind tunnel test with scaled model is one of the main ways. The wind tunnel’ s finite Re number limit the assessment of the transonic cruise drag, so we have to make the Re number effect correction for the drag of wind tunnel test. This article analyses the tolerance of wind tunnel drag measurement, and presents the wind tunnel test data basis for Re number effect correction. The constitution of transonic cruise drag is analyzed . The correct meth-od of the Min-Drag and Lift-Induced-Drag is discussed respectively, and the result is verified to get a reliable en-gineering method.