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本项目采用沈阳空气动力研究所研发的航空并行CFD计算平台,进行标准明星并行评估计算。该软件可广泛应用于飞行器的亚、跨、超和高超音速的气动力学计算和一些特殊气体动力学问题如直升机旋翼、导弹发射、座舱弹射、投弹、机动和气动弹性等。传统的飞行器气动布局设计主要依赖理论研究估算、设计师的经验以及大量的风洞试验结果,风洞试验是主要设计工具。计算机技术的迅猛发展推动了航空空气动力学的革命。目前正在大力发展的计算流体力学将以突破对黏流流场物理现象的模拟能力为重点,尤其是精确预测流动分离点和转捩过程以及湍流流动。随着中国航天航空事业的快速发展,尤其是载人航天技术的巨大成功,我国科技人员对空气动力学的数值模拟研究提出了越来越多的需求,常规的计算能力远远无法满足复杂的大型飞行器设计所带来的巨大需求。
The project uses the parallel aeronautical CFD calculation platform developed by Shenyang Aerodynamics Research Institute to carry out the parallel assessment and calculation of standard stars. The software can be widely used in Asian, Trans, Super and hypersonic aerodynamic calculation of aircraft and some special aerodynamic problems such as helicopter rotor, missile launch, cockpit ejection, bombing, maneuver and aeroelasticity. The traditional aerodynamic layout design of the aircraft mainly relies on theoretical research estimation, designer’s experience and a large number of wind tunnel test results. Wind tunnel test is the main design tool. The rapid development of computer technology has promoted the aviation aerodynamics revolution. The current development of computational fluid dynamics will focus on breaking through the simulation capability of the viscous flow field physical phenomena, especially the precise prediction of the flow separation point and transition process as well as the turbulent flow. With the rapid development of China’s space and aviation industry, especially the great success of manned space technology, our scientific and technological personnel have put forward more and more demands on the numerical simulation of aerodynamics. The conventional computing power is far from satisfying the complicated Large aircraft designed to bring the huge demand.