Unstructured grid solutions of CAWAPI F-16XL by UT SimCenter

Steve L. Karman, Brent Mitchell, Shane Sawyer, Justin Whitt

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

12 Scopus citations

Abstract

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.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
Pages8324-8351
Number of pages28
StatePublished - 2007
Externally publishedYes
Event45th AIAA Aerospace Sciences Meeting 2007 - Reno, NV, United States
Duration: Jan 8 2007Jan 11 2007

Publication series

NameCollection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
Volume12

Conference

Conference45th AIAA Aerospace Sciences Meeting 2007
Country/TerritoryUnited States
CityReno, NV
Period01/8/0701/11/07

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