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本文用壁压信息计算翼型跨音速试验时洞壁干扰修正量。计算归结为矩形域内的Dirchlet问题;利用问题的线性性,可分解为四个在矩形域的三条边界线上县齐次边界条件的Dirichlet问题,用分离变量法求解。所得四个级数的系数,其中两个由两种不同方法计算,然后加以比较,一是Mokry和Ohman的快速Fourier变换法,另一个是本文提出的递推关系式法;而另两个级数的系数本文用更直接而简单的解析积分求得,这样可使计算机时与内存要求降低。最后即可得出洞壁干扰所引起的马赫数修正和迎角修正量。试验与计算研究表明,本方法可适用于各种形式的风洞壁面情况:缝壁、孔壁和实壁。但当模型区的高阶修正量即流线曲率和压力梯度修正量增大时,则干扰量计算误差增大。
In this paper, the wall pressure information is used to calculate the correction of the wall interference in the airfoil transonic test. The Dirichlet problem, which can be attributed to the rectangular domain, is calculated. Using the linearity of the problem, the Dirichlet problem can be decomposed into four homogeneous boundary conditions on the three boundary lines of the rectangular domain. The resulting four-series coefficients, two of which are calculated by two different methods and then compared, are the fast Fourier transform of Mokry and Ohman and the recursive relational method proposed in this paper. The other two The coefficient of the number This article uses more direct and simple analytic integrals, so that the computer time and memory requirements reduced. Finally, we can get the Mach number correction and angle of attack correction caused by the wall interference. Experimental and computational studies have shown that this method can be applied to various forms of wind tunnel wall conditions: seam wall, hole wall and solid wall. However, when the higher-order correction of the model area, that is, the flow line curvature and pressure gradient correction, increases, the calculation error of the disturbance quantity increases.