The Simulation Study Of Flow Field Acive Control Base On The Adaptive Structure And Smart Skin Technique

Recent years, with the depth study of smart structure and material, and the great progresses of researches on MEMS and unsteady flow mechanism, the flow field active control combined with aerodynamics and control was brought forward. This technology is the hot spot in flow field active control research, and the adaptive wing and smart skin are the typical applications in active flow control which has great potentialities of application in improving the aerodynamic performance and suppressing the aerodynamic noise. The adaptive wing can adjust the geometry of wing profile dynamically, improve the flight performance and suppress the dynamic stall. The smart skin uses the actuator to inject the energy into the flow field to affect the structure of unsteady flow and realize the flow control, and has the advantages of high efficiency and low power loss.In this paper the theory of separation flow and vortex motion and the methods of numerical simulation and dynamic mesh technology are used to perform the flow field active control simulation which is base on the adaptive wing and smart skin technology. First, the problems were carried out the preprocess according the general processes of numerical simulation such as geometric modeling, mesh generation and so on, then the FLUENT UDF was used to compiler the embedded program which can realize the dynamic motion of model, at last the models were analyzed under different computing conditions and the results were taken comprehensive treatments. Furthermore, the feasibility and computing performance of collaborative simulation platform were studied in this paper.The results of research show that, compared with the traditional rigid deflection, the flexible deflection of adaptive wing can significantly improve the aerodynamic characteristics of wing and suppress the occurrence of stall separation. The micro scale travelling wave vibration generated by smart skin can effectively control the vortex intensity and development in flow field, and the instability of side wall flow and momentum transport between fluids have decreased under control. After exerting control, the smart skin is proved to be able to reduce the turbulent drag of the NACA0012 airfoil by 1.5%~9.8% and suppress the flow-induced noise from the cylinder at a maximum 5.4dB level in the farfield, which shows that the methods selected in this paper have a certain value for engineering application.