The Common Research Model used by the Fourth Drag Prediction Workshop was employed to investigate the accuracy of three primary codes used at The Boeing Company for transonic aerodynamic flow analysis. The codes used in this study are CFL3D (block structured), OVERFLOW (overset structured), and BCFD (unstructured). Solutions were obtained for a wing/body configuration, with the horizontal tail at incidence angles of 0, , , and with the tail removed. Grid convergence and resolution, mesh topology, and turbulence models were considered the primary factors in this study for accurate predictions of cruise drag, pitching moments, and Reynolds number effects. Also, these factors were considered in wing and tail side-of-body flow separation predictions. In this study, all three cases (one required and two optional) were completed with all three codes. The solutions were obtained with the one-equation turbulence model of Spalart and Allmaras and the two-equation shear-stress transport turbulence model of Menter. For the trim-drag and Reynolds number effect studies (optional cases), OVERFLOW and BCFD were run only with the Spalart–Allmaras turbulence model.
Reynolds-Averaged Navier–Stokes Technology for Transonic Drag Prediction: A Boeing Perspective
Journal of Aircraft ; 51 , 4 ; 1118-1134
2014-06-11
17 pages
Article (Journal)
Electronic Resource
English
Reynolds-Averaged Navier — Stokes Technology for Transonic Drag Prediction: A Boeing Perspective
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