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利用商用软件Fluent并采用四方程Transition SST模型针对NRELS809翼型在不同温度.液态水含量(LWC)、攻角等条件下所得到结冰翼型,在Re=1.0E+06时进行流场计算并得到各项气动参数。同时对结冰软件Lewice相同条件得到结冰后翼型进行对比计算,并对各实验环境因素对于翼型周围流场影响进行了对比分析,最终得出结论:实验结冰翼型与软件模拟结冰翼型气动性能差异较大,同时在霜冰生成的条件范围内,环境温度相对越高、LWC越低、攻角相对越大,其翼型的气动性能表现更好,但均低于无结冰发生翼型的气动性能。
Using the commercial software Fluent and adopting the four-way Transition SST model, the ice-formed airfoil is obtained for the NRELS809 airfoil at different temperatures, liquid water content (LWC) and angle of attack. The flow field is calculated at Re = 1.0E + 06 And get the pneumatic parameters. At the same time, the airfoil software Lewice was used to calculate the airfoil with the same conditions, and the influence of experimental environmental factors on the flow field around the airfoil was compared and analyzed. Finally, the conclusion was drawn that the experimental icing airfoil and software simulation The aerodynamic performance of the ice-wing airfoil is quite different. The aerodynamic performance of the airfoil is better than the LWC and the larger the angle of attack, under the conditions of the frost-ice formation. Aerodynamic performance of airfoil occurs.