钝头翼型和机翼跨音速绕流的渐近展开分析

本文利用渐近展开匹配法分析钝头翼型的跨音速绕流,导出了描述前缘附近流动的一级近似、二级近似下的速位方程、边界条件及相应的近似解析解,并构成关于翼表面速度的一致有效合成解,消除了跨音速小扰动近似的前缘奇性,对于大展弦比后掠翼绕流,可利用翼型绕流分析结果,消除机翼前缘奇性。     

应用于激波/边界层相互作用的非线性湍流模式

选择8个近年来有代表性的非线性湍流模式，研究2个跨声速激波／边界层相互作用问题．采用的非线性湍流模式包括4个二阶模式和4个三阶模式．2个跨声速激波／边界层相互作用的流动是轴对称圆弧突起绕流和二维管道突起流动．通过数值计算结果和实验结果的比较，对有关的非线性湍流模式进行评估和分析．计算结果表明，非线性模式的模化系数与平均流动应变不变量以及涡量不变量有关，反映了湍流的各向异性，比线性模式优越得多．     

Study of the Effect of the Depth of the Cavity of a Braking Device on the Aerodynamic Drag of a Model in Transonic and Supersonic Flow

The flowfield and the aerodynamic drag of a model consisting of a pair of bodies (leading body a cylinder and trailing body a hollow cylinder) connected by a cylindrical bar along the axis of symmetry is experimentally investigated at Mach numbers ranging from 0.6 to 1.7. In the course of the experiments, the trailing body cavity depth and the connecting bar length were varied.__________Translated from Izvestiya Rossiiskoi Academii Nauk, Mekhanika Zhidkosti i Gaza, No. 2, 2005, pp. 186–192.Original Russian Text Copyright © 2005 by Pilyugin and Khlebnikov.     

Tensor Universal Serendipity Elements and unsteady Taylor-Galerkin finite element method

A new kind of Universal Serendipity Element (USE)— the Tensor Universal Serendipity Element (TUSE) is constructed by using both tensor force finite elements and the basic idea of USE. The formulation of shape functions and their derivatives for TUSE is presented. TUSE can be used to study steady and unsteady transonic flow fields when combined with Taylor-Galerkin Finite Element Methods, the NND scheme in FDM, and four-stage Runge-Kutta methods. As numerical examples the transonic flow in cascades and one kind of complex unsteady transonic axisymmetric flow in engineering are studied. It is shown that the algorithm presented in this paper is efficient and robust. The project supported by the National Natural Science Foundation of China     

Profiling the Supersonic Part of a Plug Nozzle with a Nonuniform Transonic Flow

The effect of transonic flow nonuniformity on the profiling of optimal plug nozzles is studied in the inviscid gas approximation. Sonic and supersonic regions providing maximum thrust for given nozzle dimensions and a given outer pressure are designed for given subsonic contours and calculated nonuniform transonic flows. As in the case of uniform flow on a cylindrical sonic surface, the initial regions of the designed contours satisfy the condition that in these regions the flow Mach number is unity or near-unity. In all the examples calculated, the optimal plug nozzles produce a greater thrust than the optimal axisymmetric and annular nozzles with a near-axial flow for the same lengths and the same gas flow rates through the nozzle. It is established that contouring without regard for transonic flow nonuniformity can result in considerable thrust losses. However, these losses are due only to a decrease in the flow rate, while the specific thrust may even increase slightly.     

High-order accurate and high-resolution upwind finite volume scheme for solving euler/reynolds-averaged Navier-Stokes equations

A high-order accurate explicit scheme is proposed for solving Euler/Reynolds-averaged Navier-Stokes equations for steady and unsteady flows, respectively. Baldwin-Lomax turbulence model is utilized to obtain the turbulent viscosity. For the explicit scheme, the Runge-Kutta time-stepping methods of third orders are used in time integration, and space discretization for the right-hand side (RHS) terms of semi-discrete equations is performed by third-order ENN scheme for inviscid terms and fourth-order compact difference for viscous terms. Numerical experiments suggest that the present scheme not only has a fairly rapid convergence rate, but also can generate a highly resolved approximation to numerical solution, even to unsteady problem. The project supported by the National Natural Science Foundation of China under Contract No. 59576007 and 19572038     

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

The results of an experimental investigation of the flow past cone-cylinder bodies with small angles of the bend in the body generator at the leading corner edge (θ_s ≤ 20°) and the available data on the flow past cone-cylinder and segment-cylinder bodies with large angles of the bend in the generator (θ_{s, c} ≥ 30°) are generalized. On the basis of these data, the distinctive features of the transonic flow past these bodies and, primarily, the flow restructuring downstream of the leading corner edge at θ_s ≥ 30° are established and the characteristic gasdynamic parameters are determined. Emphasis is placed on the critical stage of flow restructuring, the nature of the stationary aerodynamic hysteresis, and the effect of the Reynolds number and wave disturbances.     

Airfoil design optimization using the Navier-Stokes equations

A design optimization technique is presented which couples a computationally efficient Navier-Stokes code with a numerical optimization algorithm. The design method improves the aerodynamic performance of an airfoil subject to specified design objectives and constraints. Recent advances in computers and compputational fluid dynamics have permitted the use of the Navier-Stokes equations in the design procedure to include the nonlinear, rotational, viscous physics of transonic flows. Using numerical optimization guarantees that a better design will be produced even with strict design constraints. The method is demonstrated with several examples at transonic flow conditions.     

转子内含激波跨声速全三元流动各类杂交命题统一的变域变分理论:(Ⅰ)势流

本文将文[1,16]所提出的各类杂交气动命题统一的变域变分原理推广到全三元亚跨声速流动,并顾及了叶面及内外壁上的抽(喷)气分布,应用变域变分工具成功地处理了全部未知边界与间断面(例如激波、自由尾涡面),将几乎全部界面条件都转化成自然条件。本文理论为叶片的气动设计与改型提供了一系列新途径,为有限元法及其它变分直接解法奠定了新的理论基础,同时也是叶片最优设计理论[6]的一个重要组成部分。