一体化高超声速飞行器气动-推进性能评估  

Evaluation of aero-propulsive performance for integrated hypersonic vehicle

作　　者：贺元元[1] 倪鸿礼[1] 乐嘉陵[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2007年第2期63-67,共5页Journal of Experiments in Fluid Mechanics

基　　金：863项目

摘　　要：吸气式高超声速飞行器的一个重要特点就是机体和推进系统的高度一体化设计。在这类高超声速飞行器的发展中,机体-推进系统内外流场相互干扰的评估以及飞行器气动-推进性能的研究是非常重要的。文中阐述了CFD和风洞试验结合评估一体化飞行器气动-推进性能的近似方法,涉及一体化飞行器进气道和发动机的三个工作状态:进气道关闭、进气道打开发动机不工作以及进气道打开发动机工作。针对进气道关闭的工作状态,大量气动数据可由试验获得。但是,受模型尺寸和设备的限制,试验模拟进气道打开发动机不工作特别是进气道打开发动机工作的飞行状态是非常困难的。因此,首先根据进气道关闭和进气道打开发动机不工作两种情况下风洞试验数据与CFD计算结果的对比得到计算误差,在此基础上,结合内外流数值模拟,预测不同进气道和发动机工作状态下一体化飞行器的气动-推进性能。Hypersonic airbreathing vehicle configurations are characterized by highly integrated propulsion flowpath and airframe systems. The assessment of propulsion-airframe flow field interactions and the integrated aero-propulsive performance of candidate systems are very important in the development of this class of hypersonic vehicle. This paper describes the approximate methods to obtain pre-flight predictions of longitudinal performance from CFD and experimental data. Three mission points are analyzed： cowl-closed, cowl-open unpowered, and cowl-open powered. For the cowl-closed configuration, a large amount of wind tunnel data can be obtained. Because of model scale and facility limitations, it is difficult to simulate the complete internal and external flow fields when the cowl-open unpowered or the cowl-open powered. Therefore, in this paper, firstly, Computational errors are determined by the eompa.rison of numerical results with experimental data for the cowl closed model and cowl open but unpowered model. These errors are then applied to develop predictions for longitudinal performance in each of the three mission phases.

关 键 词：一体化高超声速飞行器 气动-推进性能 CFD 试验数据 计算误差 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V511.1