Steady and unsteady CFD analysis of the F-16XL using the unstructured edge code
2007 (English)In: Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting, 2007, 8258-8287 p.Conference paper (Refereed)
Steady and unsteady viscous simulations of a full-scale, semi-span and full-span model of the F-16XL-1 aircraft at seven different flight Reynolds/Mach number combinations have been performed with an unstructured CFD code. The steady-state simulations are with several turbulence models of different complexity. Detached-Eddy Simulation (DES) has been used to compute the unsteady flow. The computed results are compared with public domain flight-test data. Very good agreement is demonstrated for surface pressure distribution, local skin friction and boundary velocity profiles. The different turbulence models performed almost equally well, except the Spalart-Allmaras model, which failed to predict the flow qualitatively and quantitatively. The Differential Reynolds Stress Model (DRSM) outperformed all other models when it comes to local span-wise skin friction. DES was superior over RANS modeling at the highest angle of attack, where the flow over the outer wing is separated and partly unsteady.
Place, publisher, year, edition, pages
2007. 8258-8287 p.
Computer simulation, Mach number, Mathematical models, Reynolds number, Steady flow, Unsteady flow, Viscous flow
IdentifiersURN: urn:nbn:se:kth:diva-155618ScopusID: 2-s2.0-34250795051ISBN: 1563478900ISBN: 978-156347890-1OAI: oai:DiVA.org:kth-155618DiVA: diva2:762015
45th AIAA Aerospace Sciences Meeting 2007, 8 January 2007 through 11 January 2007, Reno, NV, United States
QC 201411102014-11-102014-11-072014-11-10Bibliographically approved