跨声速弹性波场中的单侧界面问题

在具有单侧界面约束的双半平面中弹性波的传播与4个p参数有关,当它们不全为实数时,波场中同时存在体波与面波,这时的波场称为跨声速波场。Comninou和Dundurs曾用双侧解修正法把问题归结为奇异积分方程,本文则用函数方程法讨论了这个问题,给出了界面间隙分布与压力分布的显示解析解,并通过数值计算实例展示出波场的一些特征。     

应用GAO-YONG可压缩湍流模式数值模拟RAE2822翼型绕流

应用Gao-Yong可压缩湍流模式,数值模拟RAE2822二维翼型在两种不同来流情况下的跨音速粘性绕流问题.湍流模式的对流项用ROE格式离散,扩散项用中心差分格式离散,空间离散后的控制方程用多步Runge-Kutta显式时间推进格式求解.计算结果预测了翼型表面的压力系数的分布、平均速度剖面、激波的位置、马赫数等值线等情况.同时,对翼型表面激波与边界层相互干扰以及转捩问题进行分析计算,结果表明,Gao-Yong可压缩湍流模式结合适当的数值方法能够成功地模拟翼型跨音速粘性流动.最后,基于Gao-Yong可压缩湍流模式各项异性湍流粘性的机理,初步提出一种预测转捩起始位置的方法.     

An immersed boundary solver for inviscid compressible flows

In this paper, a simple and efficient immersed boundary (IB) method is developed for the numerical simulation of inviscid compressible Euler equations. We propose a method based on coordinate transformation to calculate the unknowns of ghost points. In the present study, the body‐grid intercept points are used to build a complete bilinear (2‐D)/trilinear (3‐D) interpolation. A third‐order weighted essentially nonoscillation scheme with a new reference smoothness indicator is proposed to improve the accuracy at the extrema and discontinuity region. The dynamic blocked structured adaptive mesh is used to enhance the computational efficiency. The parallel computation with loading balance is applied to save the computational cost for 3‐D problems. Numerical tests show that the present method has second‐order overall spatial accuracy. The double Mach reflection test indicates that the present IB method gives almost identical solution as that of the boundary‐fitted method. The accuracy of the solver is further validated by subsonic and transonic flow past NACA2012 airfoil. Finally, the present IB method with adaptive mesh is validated by simulation of transonic flow past 3‐D ONERA M6 Wing. Global agreement with experimental and other numerical results are obtained.     

Distinctive features of the transonic flow past a cone-cylinder body at small angles of the bend in the body generator at the leading corner edge

The distinctive features of the transonic flow past cone-cylinder bodies with small angles of the bend in the body generator at the leading corner edge are considered. The mechanism of transonic flow restructuring downstream of the edge and the associated variation of the gasdynamic parameters are studied, the reasons for the formation of aerodynamic hysteresis are established, and the effect of the length of the cylindrical part of the body is determined.     

Effect of asymmetric pulsed periodic energy supply on aerodynamic characteristics of airfoils

The possibility of controlling the aerodynamic characteristics of airfoils in transonic flight regimes by means of local pulsed periodic energy supply is considered. The numerical solution of two-dimensional unsteady equations of gas dynamics allowed determining the changes in the flow structure near a symmetric airfoil and its aerodynamic characteristics depending on the magnitude of energy in the case of its asymmetric (with respect to the airfoil) supply. The results obtained are compared with the calculated data for the flow around the airfoil at different angles of attack without energy supply. With the use of energy supply, a prescribed lift force can be obtained with a substantially lower wave drag of the airfoil, as compared with the flow around the airfoil at an angle of attack. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 48, No. 6, pp. 70–76, November–December, 2007.     

Extension of Ovsyannikov's Analytical Solutions to Transonic Flows

The solution of the equation of the velocity potential of a steady axisymmetric ideal-gas flow in the neighborhood of a given point at the axis of symmetry in the form of a double series in powers of the distance to the axis of symmetry and its logarithm is considered. Recurrent chains of equations with arbitrariness in two analytical functions of the streamwise variable are obtained for coefficients of the series. Convergence of the constructed series is proved by the method of special majorants. The theorem of existence and uniqueness of the solution of the initial-boundary problem for this nonlinear differential equation in partial derivatives with a singularity at the axis of symmetry is obtained as an analog of Kovalevskaya's and Ovsyannikov's theorems. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 46, No. 6, pp. 14–25, November–December, 2005.     

跨音速后掠翼抖振边界计算

本文提出一种确定跨音速后掠翼抖振边界的数值计算方法,现有的确定跨音速翼型抖振边界的F.Thomas 准则被推广到包括具有大后掠角的后掠翼,计算是对侧滑翼进行,其中用积分法对三维可压缩湍流边界层的计算是根据本文作者听发展的方法,对于跨音速压强分布是利用A.Eberle的解全速位方程的有限元素法给出,按本文方法计算出F-86A 飞机的抖振边界与相同雷诺数下飞行试验所得结果符合得很好。     

一个高分辨率的矢通量分裂—TVD杂交新格式

本文提出了一个新的杂交格式,它将Steger-Warming的矢通量分裂与Harten的TVD格式紧密结合在一起,构造了一个高分辨率的新格式,用于计算跨声速流场和捕获激波。典型的定常跨声速叶栅流算例表明:当Courant数取6～100时,一般在90步内残差的二范数下降三个数量级,这样的收敛率要比Beam-Warming格式快得多;观察残差的收敛历史发现:收敛曲线并无大的波动;分析激波附近的数值结果,没出现“低亏,过跳”、伪振荡现象,叶盆和叶背面上激波前或激波后的参数无波动;在60×15网格下捕获的激波过渡区不超过2个网格,表明了该格式具有较高的分辨率,能在不人为附加耗散项的条件下给出高质量无数值波动的激波流场解。     

透平叶栅跨音速流动计算中的新型有限元法

将Ｔａｙｌｏｒ－Ｇａｌｅｒｋｉｎ有限元法和多级有限元的思想结合起来，构成了在收敛速度和稳定性两方面均较好的新型有限元算法：多级广义有限元。利用这一方法，分别基于Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程和Ｅｕｌｅｒ方程，研究了透平跨音速叶栅无粘流动和粘性流动，并将计算结果与实验结果作了比较。计算结果表明，本方法是透平机械内部跨音速流动计算的强有力的手段。     

A new,high-resolution shock-capturing hybrid scheme of flux vector splitting-Harten's TVD

The paper presents a new high-resolution hybrid scheme combining implicit flux vector splitting with Harten's TVD, which is proved suitable for shock-capturing calculation in gasdynamics. Fluxsplitting procedures are applied to discretize the implicit part of the Euler equations whereas Harten's numerical fluxes are used to calculate the residual of steady-state solutions. It ensures good shock-capturing properties and produces sharp numerical discontinuities without oscillations. It excludes expansion shocks and leads only to physically relevant solutions. The block-line-Gauss-Seidel relaxation procedure (block-LGS) is used to solve the resulting difference equations. The time step and the CFL number are much larger than those in the linearized block-alternating-direction-implicit approximate factorization method (block-ADI). Numerical experiments suggest that the hybrid scheme not only has a fairly rapid convergence rate, but also can generate a highly resolved approximation to the steady-state solution. Hence scheme seems to lead to an effective nonoscillatory shock capturing method for steady transonic flow. Project Supported by National Natural Science Foundation of China