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本文对F.A.伍德华得的亚超声速位流场中组合体的气动分析方法作了进一步的研究和改进。改进表面边界条件方案中前缘涡面的处理;在翼身交接区内,采用改变机身内部过渡涡位置和纵向分块数的方法,改善了超声速流中组合体上的压力分布;采用了实用的物体表面几何处理方法,扩大了计算程序的几何描述能力。本文简要描述了机翼-机身-尾翼(包括垂尾短舱等部件)复杂组合体的压力分布和气动特性的数值计算方法,介绍了多种简单组合体和复杂组合体在亚超声速位流场中的计算结果,并与实验数据作对比。理论计算和实验数据比较一致,复杂组合体的计算结果表明,计算精度基本上能够满足初步选型设计的要求,可供实际使用。
In this paper, the aerodynamic analysis of F.A. Woodward’s sub-supersonic velocity field flowfield is further studied and improved. Improve the treatment of the leading edge vortex in the scheme of surface boundary conditions; improve the distribution of pressure in the supersonic flow by changing the position of the transition vortex inside the fuselage and the longitudinal block number in the wing body junction area; Practical geometry of the surface treatment methods to expand the calculation of the geometric description of the ability. This paper presents a brief description of the numerical calculation of the pressure distribution and aerodynamic characteristics of a complex combination of aero-fuselage-tail (including the components of a tail-nacelle). A variety of simple and complex combinations are introduced in the sub-ultrasonic bit-stream Field calculation results, and compared with the experimental data. The theoretical calculation and experimental data are consistent. The calculation results of the complex combination show that the calculation accuracy can basically meet the requirements of the preliminary selection design and can be used in practice.