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Comparison of NTF Experimental Data with CFD Predictions from the Third AIAA CFD Drag Prediction Workshop

机译：来自第三届AIAA CFD阻力预测研讨会的NTF实验数据与CFD预测的比较

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摘要

Recently acquired experimental data for the DLR-F6 wing-body transonic transport con figuration from the National Transonic Facility (NTF) are compared with the database of computational fluid dynamics (CFD) predictions generated for the Third AIAA CFD Drag Prediction Workshop (DPW-III). The NTF data were collected after the DPW-III, which was conducted with blind test cases. These data include both absolute drag levels and increments associated with this wing-body geometry. The baseline DLR-F6 wing-body geometry is also augmented with a side-of-body fairing which eliminates the flow separation in this juncture region. A comparison between computed and experimentally observed sizes of the side-of-body flow-separation bubble is included. The CFD results for the drag polars and separation bubble sizes are computed on grids which represent current engineering best practices for drag predictions. In addition to these data, a more rigorous attempt to predict absolute drag at the design point is provided. Here, a series of three grid densities are utilized to establish an asymptotic trend of computed drag with respect to grid convergence. This trend is then extrapolated to estimate a grid-converged absolute drag level.
机译：将国家跨音速设施（NTF）最近获得的DLR-F6机翼跨音速运输配置的实验数据与为第三AIAA CFD阻力预测研讨会（DPW-III）生成的计算流体动力学（CFD）预测数据库进行比较）。 NTF数据是在DPW-III之后收集的，该数据是在盲测情况下进行的。这些数据包括绝对风阻水平和与此机翼几何体关联的增量。基线DLR-F6机翼几何形状还增加了机体整流罩，从而消除了该接合区域的流动分离。包括计算得出的和实验观察到的侧面流分离气泡尺寸的比较。阻力极点和分隔气泡大小的CFD结果在网格上进行计算，这些网格代表了阻力预测的当前最佳工程实践。除了这些数据，还提供了更严格的尝试来预测设计点处的绝对阻力。在此，利用一系列的三个网格密度来建立相对于网格收敛的计算阻力的渐近趋势。然后推断该趋势以估计网格收敛的绝对阻力水平。

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