An anisotropic adaptive mesh generation technique is applied to the high-lift version of NASA's Common Research Model (HL-CRM) and to the JAXA Standard Model (JSM) for use with the 3~(rd) AIAA CFD High Lift Prediction Workshop. Adapted mesh solutions are generated on fully gapped and partially sealed variants of the HL-CRM and nacelle on and off variations of the JSM. Mesh adaptation is driven by a sizing metric that minimizes the L_p interpolation error of the solution Hessian for a given number of degrees of freedom. A few adaptive solutions using an output-based error indicator are also presented. Flow solutions are computed using a finite-element flow solver that achieves machine level convergence of the solution residuals. On the HL-CRM model adaptive mesh results are computed at two angles of attack on fully gapped and partially sealed variations of the geometry. Mesh convergence is compared between the adaptive results and results on a family of fixed meshes. In comparison to the fixed meshes, adapted meshes are found to better resolve important flow field features using fewer mesh elements and demonstrate markedly improved mesh convergence properties. On the JAXA JSM model, adaptive mesh results are computed for an angle of attack sweep and compared with fixed mesh results. The adaptive mesh results are found to provide better agreement with test data below stall. Both the fixed and adaptive mesh results are found to stall 1 to 2 degrees below the critical angle of attack measured in the test data.
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