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首页> 外文期刊>International journal of numerical methods for heat & fluid flow >CFD simulation of momentum injection control past a streamlined body
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CFD simulation of momentum injection control past a streamlined body

机译：流线型车身动量注入控制的CFD模拟

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Purpose - The purpose of this paper is to achieve high-performance aerofoils that enable delayed stall conditions and achieve high lift to drag ratios. Design/methodology/approach - The unsteady Reynolds averaged Navier-Stokes equations are employed in conjunction with a shear stress transport (k-ω) turbulence model. A control equation is designed and implemented to determine the temporal response of the actuator. A rotating element, in the form of an actuator disc, is embedded on the leading edge of NACA 0012 aerofoil, to inject momentum into the wake region. The actuator disc is rotated at different angular speeds, for angles of attack (α) between 00 and 240. Findings - Phenomena such as flow separation, wake vortices, delayed stall, wake control, etc. are numerically investigated by means of streamlines, streaklines, isobars, etc. Streamwise and cross-stream forces on the aerofoil are obtained. The influence of momentum injection parameter (ε) on the fluid flow patterns, and hence on the forces acting on the streamlined body are determined. A synchronization-based coupling scheme is designed and implemented to achieve annihilation of wake vortices. A delayed stall angle resulted with an attendant increase in maximum lift coefficient. Due to delay and/or prevention of separation, drag coefficient is also reduced considerably, resulting in a high-performance lifting surface. Research limitations/implications - The practicality of momentum injection principle requires both wide ranging and intensive further studies to move forward beyond the proof of concept stage. Practical implications - Determination of forces and moments on an aerofoil is of vital interest in aero-dynamic design. Perhaps, runways of the future can be shorter and/or more pay load can be carried by an aircraft, for the same stall speed. Originality/value - The paper describes how a synchronization-based coupling scheme is designed and implemented along with the RANS solver. Furthermore, it is tested to verify the dynamic adaptability of the wake vortex annihilation for NACA 0012 aerofoils.
机译：目的-本文的目的是获得高性能的翼型，从而使失速条件延迟并实现高升阻比。设计/方法/方法-将不稳定的雷诺平均Navier-Stokes方程与剪切应力传输（k-ω）湍流模型结合使用。设计和实施控制方程式以确定执行器的时间响应。呈执行器盘形式的旋转元件嵌入NACA 0012机翼的前缘，以将动量注入尾流区域。致动器圆盘以不同的角速度旋转，迎角（α）在00到240之间。结果-通过流线，条线数值研究了流动分离，尾流涡流，延迟失速，尾流控制等现象。 ，等压线等。获得在翼型上的沿流向和跨流的作用力。确定了动量注入参数（ε）对流体流动模式的影响，从而确定了对作用在流线型体上的力的影响。设计并实现了基于同步的耦合方案，以实现an灭涡流的an灭。延迟的失速角导致最大升力系数随之增加。由于延迟和/或防止分离，阻力系数也大大降低，从而形成了高性能的提升表面。研究局限性/含义-动量注入原理的实用性要求广泛且深入的研究，以超越概念验证阶段。实际意义-确定翼型上的力和力矩在空气动力学设计中至关重要。也许，在相同的失速速度下，未来的跑道可能更短和/或飞机可以承担更多的有效载荷。原创性/价值-本文描述了如何与RANS求解器一起设计和实现基于同步的耦合方案。此外，还进行了测试以验证尾流涡旋ation灭对NACA 0012机翼的动态适应性。

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