Unstructured Grid Solutions of CAWAPI F-16XL by UT SimCenter

Steve L. Karman Jr., Brent Mitchell, Shane Sawyer, Justin Whitt
The University of Tennessee at Chattanooga, Chattanooga, Tennessee, 37403

Viscous solutions for a F-16XL configuration are computed using the CFD tools used by and developed at the University of Tennessee SimCenter at Chattanooga. The study is performed in conjunction with a North Atlantic Treaty Organization Technical Team AVT- 113. Inviscid meshes are created using Gridgen. Viscous prismatic layers are added using a procedure that incorporates a Linear-Elastic smoothing scheme to perturb the existing mesh, creating room for the insertion of viscous layers. A vertex-centered, Reynolds averaged Navier-Stoke flow solver is used to compute seven test cases, defined by the NATO Technical Team AVT-113. Comparisons are made with available flight test data in the form of surface pressure coefficients.