排序方式: 共有11条查询结果,搜索用时 15 毫秒
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鲹科鱼类采用波状摆动可以实现非常高效的巡游游动,在受力动态平衡下以很高的速度向前游动,其性能远超传统的人造水下航行器,因此,探寻鱼体自主前游状态下流体力和前游速度的规律并建立相应的预测式具有重要的意义.在开源OpenFOAM平台和柔性体自主推进算法基础上,实现了波动鱼体自主游动的数值模拟,以NACA0012翼型为典型鱼体外形,对鲹科模式前向自主游动开展了系统的数值模拟.由已获得的栓结模型下推力标度律的启发,分别对自主巡游下的压差力系数和摩阻力系数进行标度研究.结果表明在雷诺数从500到50 000的范围内,压差力系数和摩阻力系数分别具有形式一致的标度规律,由此可根据数值结果给出定量的预测公式,进而根据两作用力的匹配关系可以导出鱼体自主前游速度的标度律,获得了根据已知的鱼体波动参数来预估巡游速度的方法.此外,探讨了雷诺数为500和50 000工况,不同摆尾幅度和频率组合下,鱼体厚弦比对于巡游的水动力标度律和前游速度的影响,并分析了不同鱼体外形对效能比的影响,发现雷诺数越高,获得最优效能比的鱼体越细长. 相似文献
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The characteristics and mechanism of unsteady aerodynamic heating of a transient hypersonic boundary layer caused by a sudden change in surface temperature are studied. The complete time history of wall heat flux is presented with both analytical and numerical approaches. With the analytical method, the unsteady compressible boundary layer equation is solved. In the neighborhood of the initial and final steady states, the transient responses can be expressed with a steady-state solution plus a perturbation series. By combining these two solutions, a complete solution in the entire time domain is achieved. In the region in which the analytical approach is applicable, numerical results are in good agreement with the analytical results, showing reliability of the methods. The result shows two distinct features of the unsteady response. In a short period just after a sudden increase in the wall temperature, the direction of the wall heat flux is reverted, and a new inflexion near the wall occurs in the profile of the thermal boundary layer. This is a typical unsteady characteristic. However, these unsteady responses only exist in a very short period in hypersonic flows, meaning that, in a long-term aerodynamic heating process considering only unsteady surface temperature, the unsteady characteristics of the flow can be ignored, and the traditional quasi-steady aerodynamic heating prediction methods are still valid. 相似文献
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以近空间尖前缘高超声速巡航飞行器的研制为背景, 作者在前一阶段采用模型理论分析方法, 陆续研究了沿微钝前缘驻点线的化学非平衡流动和气动加热相似律, 文章是上述研究的综合回顾和深化讨论.稀薄条件下, 驻点附近流动和传热出现一系列与连续流动模型不同的新特征, 超出了经典气动热预测理论的适用范围.作者建立了一个沿驻点线能量传递和转化的广义模型, 并分别推导了具有实际物理意义的边界层外离解非平衡流动判据和边界层内复合非平衡流动判据.基于这些判据构建了预测非平衡流动驻点气动加热的桥函数, 并讨论了稀薄非平衡真实气体流动和气动加热的相似律, 发现新型近空间尖前缘飞行器遭遇的气动热环境不同于传统大钝头航天器再入问题, 传统的天地换算相似准则将会失效.这些理论分析结果可为稀薄非平衡化学反应流及气动加热的实验和计算提供一个标模检验的手段. 相似文献
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Physical criterion study on forward stagnation point heat flux CFD computations at hypersonic speeds
In order to evaluate uncertainties in computational fluid dynamics (CFD) computations of the stagnation point heat flux, a physical criterion is developed. Based on a quasi-one-dimensional hypothesis along the stagnation line, a new stagnation flow model is applied to obtain the governing equations of the flow near the stagnation point at hypersonic speeds. From the above equations, the compatibility relations are given at the stagnation point and along the stagnation line, which consist of the physical criterion for checking the accuracy in the stagnation point heat flux computations. The verification of the criterion is made with various numerical results. 相似文献
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Flexible insect wings deform passively under the periodic loading during napping flight. The wing flexibility is considered as one of the specific mechanisms on improving insect flight performance. The constitutive relation of the insect wing material plays a key role on the wing deformation, but has not been clearly understood yet. A viscoelastic constitutive relation model was established based on the stress relaxation experiment of a dragonfly wing (in vitro). This model was examined by the finite element analysis of the dynamic deformation response for a model insect wing under the action of the periodical inertial force in flapping. It is revealed that the viscoelastic constitutive relation is rational to characterize the biomaterial property of insect wings in contrast to the elastic one. The amplitude and form of the passive viscoelastic deformation of the wing is evidently dependent on the viscous parameters in the constitutive relation. 相似文献
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研究了高超声速平板边界层因壁温时变引发的非定常气动热环境特征及机理.通过近似解析和数值模拟两种手段,得到了壁面热流随时问变化的完整过程.解析手段求解非定常可压缩边界层方程,将非定常响应表达成稳态解加上摄动级数的形式,在初始和最终稳态邻域分别求解,在适当的位置进行拼接,从而得到整个时间域上的解.在满足解析解假设的区域,数值结果与解析结果吻合较好,证明了所使用方法的可靠性.结果表明,非定常响应有两点显著特征:在壁温突然增加后短时间内,壁面热流方向改变,热边界层剖面在壁面附近出现了另一个拐点,这种新的剖面形状是典型的非定常特征.但是,高超声速情况下此种非定常响应存在的时间却很短,在考虑长时间气动加热的情况下,若只存在壁面温度时变的诱因,可以忽略流动中的非定常过程,当作准定常情况来处理. 相似文献
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