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Generalized Functions on Hilbert Spaces, Singular Integral Equations, and Problems of Aerodynamics and Electrodynamics

机译:Hilbert空间上的广义函数,奇异积分方程以及空气动力学和电动力学问题

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External flow suction devices are used in aerodynamics to increase the lift of an airfoil in an ideal incompressible flow [1]. When solving this problem, the airfoil is modeled by a vortical layer [2], and the external flow suction device is modeled by a sink [3]. The desired velocity field around the profile should have the following property. In a neighborhood of the sink, the velocity field should have a sink-type singularity on the external side of the airfoil (where the sink lies), and it should be smooth on the opposite side. Naturally, if the airfoil satisfies the no-flow condition on the sink side, the sink point itself is excluded from this condition. The airfoil flow problem is thereby reduced to the solution of a singular integral equation on the profile contour with right-hand side undefined at the sink point. It follows from the analysis of tangential components of the velocity field in a neighborhood of the sink on the airfoil side where the velocity field is smooth that the solution of the resulting singular integral equation should be sought in the class of functions that have a singularity of the type of 1/x at the sink point [1]. In the numerical solution of this singular integral equation by the discrete vortex method, grid points are chosen so as to ensure that the sink point is one of them, and when replacing the singular integral equation by a system of linear algebraic equations, the equation corresponding to the sink point is omitted [1]. The omitted equation is replaced by another equation, which is derived from some physical considerations. This proves to be inconvenient, since, when using several external flow suction devices, one always has to decide how to fill in the missing equations. Hence it was suggested in [4] to satisfy the no-flow condition not on the side of the airfoil, where the sink lies, but on the opposite side, where the velocity field is smooth. This approach results in the appearance of a delta function supported at the sink point on the right-hand side of the corresponding singular integral equation. Now the singular integral equation should be treated as a pseudodifferential equation in the class of distributions. A version of such interpretation for a singular integral equation with a Hilbert kernel in the class of periodic distributions was presented in [5], In this case, periodic distributions were treated as a subset of distributions on the entire real line. But this is inconvenient for singular integral equations on an interval in the class of distributions. However, it became simpler to use the discrete vortex method for the numerical solution of singular integral equations for the case in which the right-hand side contains a delta function. The method acquired the same classical form [1] as for singular integral equations in the class of absolutely integrable functions, the delta function being replaced by the corresponding step function [6].
机译:外部流动抽吸装置用于空气动力学中,以增加理想的不可压缩流动中的翼型升力[1]。解决此问题时,机翼由旋涡层[2]建模,外部引流装置由水槽[3]建模。轮廓周围的所需速度场应具有以下属性。在水槽附近,速度场在翼型的外侧(水槽所在的位置)应具有水槽型奇点,并且在相反的一侧应保持光滑。自然地,如果翼型件满足沉侧的不流动条件,则沉点本身被排除在该条件之外。从而将翼型流动问题简化为轮廓轮廓上的奇异积分方程的解,其中右手侧在下沉点处未定义。通过对翼型侧汇点附近的速度场的切向分量进行分析,在该区域速度场是光滑的,应在奇异性为的函数类别中寻找所得奇异积分方程的解。汇点[1]处的1 / x类型。在用离散涡旋方法对该奇异积分方程进行数值解时,选择网格点以确保汇点是其中之一,当用线性代数方程组代替奇异积分方程时,该方程对应到沉点的省略[1]。省略的方程式由另一个方程式代替,该方程式是从某些物理考虑因素得出的。事实证明,这样做很不方便,因为在使用多个外部吸流装置时,总是必须决定如何填写缺失的方程式。因此,在[4]中提出要满足不流动条件,而不是在机翼一侧(沉陷所在的位置)而不是在另一侧(速度场是光滑的)满足。这种方法的结果是在相应的奇异积分方程右侧的汇点处支持了增量函数。现在,将奇异积分方程视为分布类别中的伪微分方程。在文献[5]中给出了一个关于具有希尔伯特核的奇异积分方程的解释版本,在这种情况下,周期性分布被视为整个实线上分布的子集。但这对于分布类别中某个区间上的奇异积分方程式是不方便的。但是,对于右侧包含德尔塔函数的情况,使用离散涡旋方法求解奇异积分方程的数值解变得更加简单。该方法获得了与绝对积分函数类别中的奇异积分方程式相同的经典形式[1],其中δ函数被相应的阶跃函数[6]取代。

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