中文摘要：

由于风洞实验的成本过高，模型变形测量实验中标记点对气动特性的影响研究一直被忽略，从而增加了气动力数据的不确定度。基于CFD方法通过3个不同条件下的Case研究了标记点对超临界翼型RAE2822气动力的影响规律。CaseⅠ中研究了标记点厚度从3H到9H变化和弦向位置从0．1到0．9变化对气动特性的影响；CaseⅡ中研究了模型迎角从-4°到8°变化标记点对气动特性的影响；CaseⅢ中研究了4种不同的标记点组合方式在标记点厚度从1H到9H的范围内对气动特性的影响。计算结果表明标记点对模型气动特性的影响对标记点位置特别敏感，影响量随标记点厚度的变化呈现非线性特性。气动力影响量随迎角变化的计算结果表明，在模型迎角为正的条件下，标记点粘贴在下表面比粘贴在上表面对气动特性的影响要小很多。

英文摘要：

Target influence on aerodynamic characteristics in video model deformation experiments has been ignored for high cost of wind tunnel tests, which causes an increase of uncertainty of aerodynamic force data. With the use of computational fluid dynamics, target influence on aerodynamic characteristics of the airfoil RAEE2822 was investigated through three cases to find the influence rules of different parameters. In caseⅠ , influence of target thickness ranging from 3H to 9H and target chordwise location ranging from 0.1 to 0.9 on both side surfaces of the airfoil was investigated. In case Ⅱ, influence of angle of attack ranging from -4° to 8° was investigated. In case Ⅲ, influence of four combination types of targets were investigated with the target thickness ranging from 1H to 9H. Computational results show that the target influence is sensitive to chordwise location and the relation between variation of aerodynamic force and target thickness is nonlinear. Aerodynamic force variation results of different angles of attack also indicate that influence of target on low surface is much smaller than that of target on upper surface when model has a positive angle of attack.