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    simpleFoam求解NACA0012翼型

    OpenFOAM
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      ycx1042341217 last edited by

      学生在用simpleFoam 求解NACA0012翼型的升力系数和阻力系数时,所得结果Cd100多,Cl 20多。学生采用速度1.6m/s,攻角8度,弦长1m,SA模型。U文件中入口和出口类型均为freestream,翼型为fixedValue;P文件中入口和出口类型均为 freestreamPressure;nut和nuTlida文件中参数为0.14。controlDict文件密度输入1.225,lref1,aref0.08。学生是刚学习openfoam,很多东西还不是很清楚。请各位老师帮忙看一下问题出在哪里,不胜感谢!

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