High performance numerical methods for fluid-structure interaction problemds in aeronautics

解决航空领域流固耦合问题的高性能数值方法

• 批准号: 132923-2006
• 负责人: Soulaïmani, Azzeddine
• 金额: $ 2.19万
• 依托单位: École de technologie supérieure
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2008
• 资助国家: 加拿大
• 起止时间: 2008-01-01 至 2009-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=391368
• 关键词: performance; numerical; methods; fluid; structure

Aeroelasticity is the study of the mutual interactions between an air flow and a flexible structure. It is one of the most important and challenging multi-physics applications. It couples two nontrivial applications and is characterized by multi-scale phenomena, both in space and time. The efficient solution to this problem is of critical importance to the design of aircraft. In addition to aerodynamics performance, acoustical effects are becoming an important issue in aeronautics, especially for the design of helicopter blades. Consequently, acoustical data has to be generated as well as aerodynamic and aeroelastic data. We propose an interdisciplinary project to address some of the challenging issues which arise in fluid-structure interaction problems with applications to aircraft wings and helicopter rotors. This field of study blends solution methods from fluid dynamics, structures and acoustics. Therefore, as prerequisite, good numerical methods for both of these areas must be developed. A first goal of this work is to consider the simulation of fluid flow around complex 3D geometries using unsteady Euler and Navier-Sokes equations with the Spalart-Allmaras (SA) turbulence model. We plan on developing a proper discretization of the SA equations. A second goal is to solve the nonlinear problem which arises in the coupling between aerodynamics and structures. We develop efficient algorithms for coupling the subsystems. A third goal is to apply the developed aeroselasticity technology to perform flutter simulations for isolated wings and wing-body configurations. A forth goal is to extend these applications to flexible blades. The flow induced oscillations on the rotor will be computed to understand structural loading conditions and their effects on helicopter aerodynamics performance and noise generation. A fifth goal is to develop numerical methods for noise generation and propagation by rotorcraft.

气动弹性是研究气流和柔性结构之间的相互作用。它是最重要和最具挑战性的多物理场应用之一。它耦合了两个非平凡的应用，其特点是多尺度现象，在空间和时间。这一问题的有效解决对飞机的设计至关重要。除了空气动力学性能外，声学效应也成为航空领域的一个重要问题，特别是对于直升机桨叶的设计。因此，声学数据以及空气动力学和气动弹性数据必须生成。我们提出了一个跨学科的项目，以解决一些具有挑战性的问题，出现在飞机机翼和直升机旋翼的应用程序中的流体-结构相互作用的问题。该研究领域融合了流体动力学，结构和声学的解决方案。因此，作为先决条件，良好的数值方法，这两个领域必须制定。这项工作的第一个目标是考虑使用非定常欧拉和Navier-Sokes方程与Spalart-Allmaras（SA）湍流模型模拟复杂的三维几何形状周围的流体流动。我们计划开发一个适当的离散SA方程。第二个目标是解决在空气动力学和结构之间的耦合中出现的非线性问题。我们开发有效的算法耦合的子系统。第三个目标是应用已开发的气动弹性技术对孤立机翼和翼身组合体进行颤振模拟。第四个目标是将这些应用扩展到柔性叶片。将计算旋翼上的流致振荡，以了解结构载荷条件及其对直升机空气动力学性能和噪声产生的影响。第五个目标是发展旋翼机噪声产生和传播的数值方法。