Numerical simulation of high Reynolds number turbulent flow around a Bell 214 ST helicopter fuselage is performed using an unstructured mesh. The computations include an application of Reynolds Stress Model (RSM), which consists of coupling the Reynolds transport equations with the Favre averaged Navier-Stokes Equations. The resulting system of 12 coupled, non-linear partial differential equations is solved using PUMA_RSM which is an in-house unstructured grid computational fluid dynamics code written in ANSI C++. In order to reduce the CPU time and memory requirements, parallel processing is applied with the MPI (Message Passing Interface) communication standard. Solutions are performed for an isolated fuselage at three different flow conditions and helicopter with rotors modeled using momentum theory in forward flight. Predicted pressure and drag force correlate well with the wind tunnel data and RSM is proved to be useful for turbulent flow around such a complex geometry.
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机译:使用非结构化网格进行钟罩214 ST直升机机身周围的高雷诺数湍流的数值模拟。计算包括reynolds应力模型(RSM)的应用,其包括将Reynolds传输方程与Favre平均的Navier-Stokes方程联接。使用PUMA_RSM解决了12个耦合的12个耦合的非线性部分微分方程的系统,其是在ANSI C ++中写入的内部非结构化网格计算流体动力学代码。为了降低CPU时间和内存要求,并行处理应用MPI(消息传递接口)通信标准。在三种不同的流量条件下对隔离机身进行解决方案,直升机,带有在向前飞行中使用动量理论建模的转子。预测压力和拖动力与风洞数据相互作用,并且证明RSM对于这种复杂几何形状周围的湍流是有用的。
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