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为了改善高超声速飞行器的外形气动特性,以高超声速条件下锥型流近似解为基础,提出了一种高超声速乘波构型的初步设计方案,并由此方案生成乘波体外形。在确定Ma=6锥型流场之后,对于不同的乘波体长细比和底部基线参数进行了外形设计,并就参数变化对乘波体设计外形的影响进行了讨论,得到了设计参数影响外形的基本规律。运用Fluent软件对于所设计的乘波体外形进行三维流场数值模拟,分析其在设计状态下的绕流流场特性;并对乘波体在非设计马赫数以及非设计攻角状态下进行数值模拟,分析其在非设计状态下的气动特性的变化。结果表明:数值模拟结果与设计理论相吻合,压强与密度云图均显示了本文所设计的乘波构型的乘波特征,并且在非设计工况下其乘波特征仍然显著,例如Ma=4。
In order to improve the aerodynamic characteristics of hypersonic vehicles, based on the approximate solution of cone flow in hypersonic conditions, a preliminary design scheme of hypersonic multiplicative wave configuration was proposed. After the Ma = 6 cone flow field is determined, the contour design of different multipath sowing ratio and bottom baseline parameters are discussed. The influence of the parameter variation on the design shape of the multiplier body is discussed. The influence of design parameters is obtained The basic rules of appearance. Fluent software is used to simulate the three-dimensional flow field of the designed wave multipurpose shape and to analyze the flow field characteristics of the flow field in the designed state. Numerical calculations of the multiplicative wave body at non-designed Mach number and non-design angle of attack Simulation, analysis of its non-design changes in the aerodynamic characteristics. The results show that the numerical simulation results are in good agreement with the design theory. Both the pressure and density cloud images show the characteristics of the multiplication wave in the designed wave multiplication structure and the characteristics of the multiplication wave are still significant under non-designed conditions. For example, Ma = 4 .