跨音速小扰动方法在飞机复杂组合体计算上的应用  

The TSP Methods Applied to the Calculation of Transonic Flow about Wing/Body/Nacelle/Pylon-Configurations

作　　者：王蝶茜 SvenG.Hedman 

机构地区：[1]西北工业大学 [2]瑞典航空研究院理论空气动力部

出　　处：《西北工业大学学报》1990年第2期121-131,共11页Journal of Northwestern Polytechnical University

摘　　要：一个局部区域的柱坐标网格嵌入一个总体笛卡坐标系网格中,此两网格系统在一个公共区中互相复盖,一个网格系统在此相互复盖的公共区中的速势值作为另一网格系统计算时的边值条件。对于机翼机身发动机吊舱和挂架飞机组合体,发动机吊舱和挂架的物面边界条件在柱坐标系中表达而机翼机身物面边界条件则在笛卡坐标中表达。机翼机身计算的位流方程的假设前提是所有扰动速度相对于远前方未扰动速度为高阶小量,而模拟发动机吊舱的小扰动方程则允许可与自由流相比拟的纵向扰动速度。与方程相一致的质量流边界条件改进了解的准确性和数值计算的收敛和稳定。发动机喷流在本文中得到模拟。算例为M_∞=0.3和0.75下的近代客机,计算结果与实验进行了比较,可见本方法能十分成功地预示飞机复杂组合体流场的基本特征。In order to make clear the contribution of this paper, it is necessary toreview research work on this topic and to give a concise summary of theauthors' research. Due to the mixed character of transonic flow, load determination by theapproaches emphasizing the use of more exact flow equations is quite difficultfor complex configurations [1, 2, 3, 4] and requires further development. TSP(Tran-sonic Small Perturbation) methods are cost-effective in repeated nu-merical calculations for complex geometries such as wing/body/nacelles (orstores)/pylons configurations. Quite a number of papers on TSP methods areavailable [5, 6, 7]. The improvement in accuracy obtained by the authors comes from abetter simplified model for TSP computation. In other TSP methods like thestandard Guderley-von-Karman, NASA, RAE, NLR and Dornier forms they triedto improve the TSP method. Some of them presented very elegant ways of derivingsmall disturbance forms and achieved certain success [8]. None of them can be com-patible with the leading edge (or lip) boundary condition and with large longitu-dinal disturbance velocity for intake flow field, but in this paper the smalldisturbance equation used for nacelle Calculation can. Besides, a mass fluxboundary condition which is consistent with the equation is used here insteadof a commonly used velocity boundary condition Furthermore, the boundarycondition is expressed in terms of the tangential velocities at contour obtainedthrough directional derivaties to avoid using dummy potential which is commonlyused in other TSP papers. These improve the pressure distribution accuracy and convergence as well. Available forms based on TSP methods for nacelle/pylon flow are, in theauthors' opinion, as yet not as accurate as is needed in aircraft design. Thenew contribution of this paper is believed to be that more accurate results fornacelle/pylon flow are obtained. Pressure distributions have been computed and compared with experimentaldata for a configuration resembling a modern commercial airliner at two

关 键 词：飞机 复杂组合体 流场 跨音速 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]