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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。Case I中研究了标记点厚度从3 H到9 H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;Case III中研究了4种不同的标记点组合方式在标记点厚度从1 H到9 H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。
Due to the high cost of wind tunnel experiments, the influence of the marked points on the aerodynamic characteristics in the deformation measurement experiment has been neglected, which increases the uncertainty of the aerodynamic data. Based on the CFD method, the influence of the marked points on the aerodynamic force of supercritical airfoil RAE2822 was studied by three cases under different conditions. Case I, we studied the effect of the change of the thickness of the marker point from 3 H to 9 H on the aerodynamic characteristics from 0.1 to 0.9, In Case III, the effects of four different combinations of points on the aerodynamic characteristics in the range of 1 H to 9 H of the mark thickness were studied. The calculation results show that the influence of the mark point on the aerodynamic characteristics of the model is particularly sensitive to the position of the mark point, and the influence quantity shows a nonlinear characteristic with the change of the mark point thickness. The calculation results of the aerodynamic influence with the angle of attack show that the effect of the mark on the lower surface is much less than that on the upper surface under the positive attack angle of the model.