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Aerodynamic Modeling of Lifting Surfaces Accounting for Synthetic Jet Actuators

机译:合成射流作动器的举升表面的空气动力学建模

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This paper contributes to the development and validation of reduced order unsteady aerodynamic models of lifting surfaces accounting for Synthetic Jet Actuation (SJA). SJAs located within a lifting surface have the ability to manipulate the nearby airflow making them very attractive for a number of applications, in particular flow separation and aeroelastic control. Recent results have shown that SJAs can allow lifting surfaces to carry loads without flow separation at much higher angles-of-attack then the counterpart without jet actuation. In addition, even at small angle-of-attack, the actuators energize the flow in the boundary layer, directly contributing to the airfoil "dynamic virtual shaping" that enhances the performance of the lifting surface. The flow structure of a lifting surface with a SJA is quite complicated and so far the characterization of such structure, at all scales, has been done primarily by means of CFD computations or experiments. However, when the interest is limited to the determination of global aerodynamic properties, that is, unsteady aerodynamic lift and moment, it is possible to characterize the flow around the lifting surface with SJAs through reduced order models (ROMs). This paper extends a prior effort of the authors, providing a better understanding of the validity of two ROMs: the Unsteady Theodorsen's based SJA Model (T-SJA) and the Unsteady Doublet Panel SJA Model (UDP-SJA). To validate the T-SJA and the UDP-SJA models, CFD have been employed. A number of parameters, such as airfoil thickness, jet location and frequency of actuation will be considered for a static airfoil at zero angle-of-attack. This parameter space enables one to estimate the region in which ROMs are valid. In addition, this paper aims to extend the validity of such ROMs as to account for thickness effects as well as to empirically correct the aerodynamic loads for positions of the jet toward the leading and trailing edges, where ROMs could potentially break down.
机译:本文为合成表面喷气致动(SJA)的升力面的降阶非定常空气动力学模型的开发和验证做出了贡献。位于举升表面内的SJA具有操纵附近气流的能力,使其对于许多应用特别有吸引力,特别是在流分离和气动弹性控制方面。最近的结果表明,与没有喷射驱动的情况相比,SJA可以使举升表面承受载荷,而没有在较大的攻角下进行流动分离。此外,即使在较小的攻角下,执行器也能为边界层中的流体提供能量,直接有助于机翼“动态虚拟成形”,从而增强了提升面的性能。带有SJA的提升面的流动结构非常复杂,到目前为止,主要通过CFD计算或实验对这种结构进行了各种规模的表征。但是,当人们的兴趣仅限于确定整体空气动力特性,即不稳定的空气动力升力和力矩时,可以通过降阶模型(ROM)用SJA表征升力表面周围的流动。本文扩展了作者的先前工作,从而更好地理解了两个ROM的有效性:基于非稳定Theodorsen的SJA模型(T-SJA)和非稳定Doublet Panel SJA模型(UDP-SJA)。为了验证T-SJA和UDP-SJA模型,已使用CFD。对于零攻角的静态机翼,将考虑许多参数,例如机翼厚度,射流位置和致动频率。通过此参数空间,可以估计ROM有效的区域。此外,本文旨在扩展此类ROM的有效性,以考虑厚度影响,并凭经验校正喷头朝向前缘和后缘的射流位置的空气动力学载荷,在此情况下ROM可能会损坏。

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