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首页> 外文期刊>Journal of the American Helicopter Society >Unsteady Aerodynamics of an Airfoil/Flap Combination on a Helicopter Rotor Using Computational Fluid Dynamics and Approximate Methods
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Unsteady Aerodynamics of an Airfoil/Flap Combination on a Helicopter Rotor Using Computational Fluid Dynamics and Approximate Methods

机译：基于计算流体力学和近似方法的直升机旋翼/襟翼组合的非定常空气动力学

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The ability to model accurately and efficiently unsteady aerodynamic effects for actively controlled trailing-edge flaps (ACFs) is crucial for practical application of such systems for vibration and noise reduction as well as performance enhancement. Two-dimensional unsteady airloads due to oscillating flap motion are calculated and compared using various computational fluid dynamics (CFD) codes and a CFD-based reduced-order model (ROM). This ROM is based on the rational function approximations approach, which yields a state-space, time-domain aerodynamic model suitable for incorporation into comprehensive rotorcraft simulation codes. The accuracy of this model is demonstrated across a practical range of unsteady flow conditions encountered by active flaps. Two Reynolds-averaged Navier-Stokes solvers (CFD++ and OVERFLOW) are employed in conjunction with various turbulence models, including large eddy simulation based models, so as to examine code independence. Flow physics associated with three-dimensional effects, flap hinge gap, as well as compressibility effects are also examined.
机译：为主动控制的后缘襟翼（ACF）准确而有效地对非定常空气动力学效应进行建模的能力对于此类系统的减振降噪和性能提升的实际应用至关重要。使用各种计算流体动力学（CFD）代码和基于CFD的降序模型（ROM），计算并比较了由于襟翼摆动引起的二维非定常空气载荷。该ROM基于有理函数逼近方法，可生成状态空间，时域空气动力学模型，适合于纳入全面的旋翼飞机仿真代码中。在活动襟翼遇到的不稳定流量的实际范围内，证明了该模型的准确性。两个雷诺平均的Navier-Stokes求解器（CFD ++和OVERFLOW）与各种湍流模型（包括基于大型涡流仿真的模型）结合使用，以检查代码的独立性。还研究了与三维效应，襟翼铰链间隙以及可压缩性效应相关的流动物理学。

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