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以风力机DU93-W-210翼型为研究对象,采用数值计算与实验验证方法研究了低雷诺数(2×105~5×105)下翼型升阻气动性能,基于修正转捩模型分析了多雷诺数多攻角下翼型层流分离泡对气动性能的影响.结果表明:基于四方程转捩模型Transition SST计算所得升阻力系数及翼型表面转捩位置与实验值接近,低雷诺数流动计算适用性较好;雷诺数越小,翼型层流分离泡越明显,翼型升阻比越小;失速前雷诺数对翼型升阻比影响较大而失速后影响较小,且雷诺数越小该翼型失速越缓和;攻角越大,翼型上表面层流分离泡越靠近前缘而下表面越靠近尾缘;失速前上表面和下表面转捩位置均呈线性变化,失速后上表面转捩位置呈非线性变化.
Based on the airfoil DU93-W-210 airfoil, the aerodynamic performance of airfoil drag-up with low Reynolds number (2 × 105 ~ 5 × 105) was studied by numerical calculation and experimental verification. Based on the modified model, The results show that the coefficient of lift resistance and the surface transition of the airfoil based on the four-equation Transition SST are close to the experimental values, and the low Reynolds number The smaller the Reynolds number is, the more obvious the airfoil splitting bubble is, the smaller the lift-drag ratio of airfoil is. The Reynolds number before stall has a greater influence on lift-drag ratio of airfoil but less after stalling, and The smaller the Reynolds number is, the finer the airfoil stalling. The larger the angle of attack, the closer the laminar flow of upper airfoil splits to the leading edge and the lower surface closer to the trailing edge. The position of the upper surface and lower surface of the airfoil changes linearly , After stalling the surface of the upper surface of the transition was non-linear changes.