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首页> 外文期刊>Journal of Aeronautics, Astronautics and Aviation, A >Application of the Sliding Mesh Technique for Helicopter Rotor Flow Simulation
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Application of the Sliding Mesh Technique for Helicopter Rotor Flow Simulation

机译：滑动网格技术在直升机旋翼流动仿真中的应用

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Rotors are the source of the lifting force for helicopters. The rotors mounted at the top of the fuselage revolve to generate air pressures both above and under the airfoil, resulting in a pressure gradient which enables the aircraft to fly when the lift from below exceeds its weight. In the meanwhile, influenced by the downwash airflow and vortex arising from the rotor spinning, the flow field around the rotor becomes complex and unpredictable. Because of the difficulty of measuring rotor-related flow field data under laboratory conditions, this study attempts to simulate the flow field of the rotor by means of a numerical simulation, and compute the forces received at different parts of the airfoil surface. To accurately simulate the minute flow field phenomena when the rotor is in motion, this study employed the Sliding Mesh Model (SMM) to simulate the revolving movement of the rotor. The flow field around the rotor was numerically calculated using the Finite Volume Method (FVM). In addition, with respect to the accuracy and stability of the numerical simulation, this study has carried out an in-depth investigation and analysis using varying mesh numbers and time step settings. By comparing and verifying the results of numerical simulation against the experimental data, it was confirmed that the numerical computation model presented in this study could be effectively applied to flow field analysis for helicopter rotors, as well as to their configuration designs.
机译：旋翼是直升机起升力的来源。安装在机身顶部的旋翼旋转以在机翼上方和下方产生气压，从而产生压力梯度，当从下方升起的飞机超过其重量时，该压力梯度可使飞机飞行。同时，受转子旋转产生的向下冲洗气流和涡流的影响，转子周围的流场变得复杂且不可预测。由于在实验室条件下难以测量与转子相关的流场数据，因此本研究试图通过数值模拟来模拟转子的流场，并计算在机翼表面不同部位承受的力。为了准确地模拟转子运动时的微小流场现象，本研究采用了滑动网格模型（SMM）来模拟转子的旋转运动。使用有限体积法（FVM）对转子周围的流场进行数值计算。此外，关于数值模拟的准确性和稳定性，本研究使用可变的网格数和时间步长设置进行了深入的研究和分析。通过将数值模拟结果与实验数据进行比较和验证，可以确认本研究中提出的数值计算模型可以有效地应用于直升机旋翼的流场分析及其结构设计。

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