SU2学习笔记
摘要：
该文档是 2014 年斯坦福大学 SU2 v3.2.2 版本代码参考手册，由 Doxygen 工具生成。手册目录完整罗列程序模块、类、文件索引，系统介绍对流项、黏性项、源项离散以及势流、欧拉、纳维 - 斯托克斯、湍流方程求解模块。文档收录大量求解器、流场变量、梯度、网格自适应、几何处理等 C++ 核心类，逐一记录各类构造、析构、成员函数与数据成员，覆盖边界条件、并行计算、网格变形、FFD 几何变形、线性预处理等底层接口，清晰呈现 SU2 开源 CFD 程序模块化代码结构与数值算法实现逻辑，可用于程序二次开发、气动优化算法研究与代码调试参考。
Abstract 软件概述:
The Stanford University Unstructured (SU2 ) suite is an open-source collection of C++ based software tools for performing Partial Di优erential Equation (PDE) an alysis and solving PDE con- strained optimization problems. The toolset is designed with computational fiuid dynamics and aerodynamic shape optimization in mind, but is extensible to treat arbitrary sets of governing equations such as potential fiow, electrodynamics, chemically reacting fiows, and many other- s. SU2 is under active development in the Aerospace Design Lab (ADL) of the Department of Aeronautics and Astronautics at Stanford University, and is released under an open-source license.
Chapter 1 Introduction
1.1 Overview
The SU2 software suite specializes in high fidelity PDE an alysis and design of PDE constrained systems on unstructured domains. The suite itself is composed of several C++ ana lysis modules that handle specific tasks, including the solution of the PDE system, decomposition of the domain for parallel computations, grid deformation, and many other tasks required for shape optimization and sensitivity studies. Some specifics of these modules can be found on the SU2 Tools page of this documentation with more complete information available in the Developer’s Guide. The current development of this code is done by the Aerospace Design Lab at Stanford University, based on the original structure of CADES 1.0 (2009 - 2010).
The software structure has been designed for maximum flexibility, leveraging the class- inheritance features native to the C++ programming language. This makes SU2 an ideal vehicle for performing multi-physics simulations, including multi-species thermochemical non- equilibrium flow an alysis, combustion modeling, two-phase flow simulations, magnetohydrody- namics simulations, etc. Additionally, the decomposition of the flow solver allows for the rapid implementation of new spatial discretization methods and time-integration schemes.
1.1.1 PDE An alysis
SU2 is ideally suited to perform high fidelity, PDE an alysis over complex geometries using un- structured mesh technology. The solver, SU2 CFD, is vertex-centered and finite-volume based. It currently offers the following schemes for spatially discretizing a range of governing equations:
• Jameson-Schmidt-Turkel or JST (centered scheme, second-order accurate in space).
• Lax-Friedrich (centered scheme, first-order accurate in space).
• Roe 1st-Order (upwind scheme, first-order accurate in space).
• Roe 2nd-Order (upwind scheme, second-order accurate in space using MUSCL scheme and Venkatakrishnan’s limiter).
For time integration (explicit, and implicit), SU2 offers the following schemes:
• Backward and forward Euler (first-order accurate in time).
• Runge-Kutta Explicit (up to fourth-order accurate in time).
• Dual time stepping (second-order accurate in time).
Other integration schemes are currently under development, and the class structure of SU2 makes adding new schemes simple. Convergence acceleration and robustness enhancement fea- tures are available such as agglomeration multigrid schemes and residual smoothing. SU2 can
Figure 1.2: Pressure contours (left) and the unstructured surface mesh (right) on the DLR F6 wing-body configuration.
also execute in parallel for large-scale simulations using a Message Passing Interface (MPI) im- plementation. More details and specifics are available in the SU2 Tools and the Developer’s Guide.
Reynolds Averaged Navier-Stokes (RANS), Laminar Navier Stokes & Euler Simu- lations
The current release of SU2 comes pre-packaged with the Reynolds Averaged Navier-Stokes (with the Spalart-Allmaras turbulence model), laminar Navier-Stokes, and Euler equations (a- mong others) to perform a wide range of general fluid dynamics an alysis problems. Solutions from the software suite for a variety of configurations spanning the subsonic, transonic, super- sonic, and hypersonic flight regimes are shown throughout this page to highlight the capabilities of the code.
Rotating Frame Simulations
A rotating frame formulation of the Euler equations is included in SU2 for efficient, steady an alysis of inviscid fluid around rotating aerodynamic bodies. Potential applications include wind turbines, turbomachinery, propellers, open-rotors, helicopter rotors, etc.
Multi-Physics Simulations
The general formulation of the solution vector in the CFD module permits the rapid implementation of additional governing equation sets and source terms to accommodate multi-physics simulations with ease. Results from a coupled electric potential, inviscid flow an alysis is shown here for a multi-species Argon gas mixture with charge separation.
Optimal Shape Design
The design optimization of PDE constrained systems is a primary function of the SU2 suite.
The built-in adjoint solver in the CFD module, in conjunction with the Gradient Projection Code (GPC), and Mesh Deformation Code (MDC) deliver surface sensitivities and objective function gradients to Scipy-based optimization algorithms, enabling surface shape optimization for complex geometries. Furthermore, both the flow and adjoint solvers within SU2 can be executed in parallel within the design loop for increased computational efficiency. Each of the design examples on this page take advantage of the Euler and Adjoint-Euler flow solvers in parallel with the design process driven by SciPy optimizers. Constraints such as a minimum lift or maximum moment can also be included.
Adaptive Mesh Refinement
The Mesh Adaptation Code (MAC) in the SU2 suite facilitates strategic mesh adaptation based on several common schemes, including gradient and adjoint-based methods.
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