ICEM+FLUENT超声速弹翼气动特征仿真分析
时间:2018-06-03 15:34 来源:毕业论文 作者:毕业论文 点击:次
| 摘要现代化战争的形式越来越趋于立体化，所以对超声速导弹的威力和准确度要求越来越高，这就意着超声速弹翼必须具有较高的机动特性，具备较大的法向过载，也就是说超声速导弹的主升力面需要能够产生足够的法向力，同时也需要提高导弹的升阻比。超声速弹翼是超声速战术导弹的主要升力面，国内外的研究资料表明超声速弹翼的设计对提高导弹的机动性、降低导弹所受阻力、保证导弹飞行稳定至关重要。超声速弹翼的升力系数、阻力系数、升阻比跟超声速弹翼的展弦比、根稍比、等效后掠角、翼面厚度、翼剖面形状等几何设计参数以及飞行Ma数、飞行所带攻角有关。本文通过使用UG、ICEM、FLUENT等软件进行超声速弹翼的三文模型建立、网格划分、数值仿真分析，研究上述参数对超声速弹翼的升力系数和阻力系数的影响，并在此基础上讨论各种几何参数配置的翼面的优缺点。23710 关键词 超声速弹翼 飞行马赫数 升力系数 阻力系数 毕业设计说明书（毕业论文）外文摘要 Title Supersonic wing aerodynamic characteristics simulation analysis Abstract: Form of modern warfare are more and more three-dimensional, so supersonic missile power and accuracy of the increasingly high demand, this means that the supersonic wing must have a high mobility characteristics, have a larger normal overload, that is the main lifting surface supersonic missiles need to be able to produce enough normal force, but also the need to improve the missile lift-drag ratio. Supersonic wing is the main lifting surface supersonic tactical missile, domestic and foreign research data shows that supersonic wing design is crucial to improve the maneuverability of missiles, missile suffered lower resistance, to ensure the stability of missile flight. Supersonic wing lift coefficient, the drag coefficient, lift-drag ratio with supersonic wing aspect ratio, the root is slightly more than the equivalent sweep, airfoil thickness, airfoil shape geometric design parameters and flight Mach number, the flight of the related with the angle of attack. In this paper, through the use of UG, ICEM, FLUENT software for three-dimensional model of supersonic wing establishment, meshing, numerical simulation, research the effects of these parameters on the lift and drag coefficients of supersonic wing, and discuss the advantages and disadvantages of various geometric parameters on the basis of an airfoil. Keywords Supersonic wing Flight Mach Lift coefficient Drag coefficient 目 次 1 引言 1 1．1 国外超声速导弹及弹翼研究现状 1 1.1.1 美国超声速导弹研究现状 2 1.1.2 俄罗斯超声速导弹研究现状 2 1．2 国外超声速导弹及弹翼发展经验与趋势 4 1.3 本文研究的项目和问题 5 2 研究任务说明 6 2.1 设计任务说明 6 2.2 设计任务要求与原则 6 2.3 设计参考依据 6 2.3.1 翼面在弹身周侧的布置形式 7 2.3.2 翼面沿弹身纵轴的布置形式 8 2.3.3 与机动性有关的弹翼几何参数 9 3超声速弹翼三文几何建模 14 3.1本文超声速弹翼的设计方案 14 (责任编辑：qin) |