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摘要
Simulation results for the Common Research Model transport aircraft performed for the Fourth Drag Prediction Workshop using the unstructured computational fluid dynamics code NSU3D are presented. The solution algorithms employed in NSU3D for this study are described along with examples of convergence history. The Common Research Model aircraft configuration used for the workshop consists of the wing, body, and horizontal tail with no vertical tail or engine nacelles. The computational meshes for this study were provided by NASA Langley Research Center and were prepared with the VGrid package. A complete lift-drag polar is produced in NSU3D on a baseline mesh along with additional runs on refined and coarsened meshes to assess sensitivity to grid resolution. The effect of horizontal tail angle on the drag polar is investigated and the trimmed drag polar calculated. A range of Mach number values are evaluated, and the drag polar and drag rise curves are presented. The effect of Reynolds number is assessed by comparing computed results at Reynolds numbers of 5 million and 20 million.
- 出版日期2014-8
