Simulation of 3D unsteady incompressible flow past a NACA 0012 wing section
2012 (English)Report (Other academic)
We present computational simulations of three-dimensional unsteady high Reynolds number incompressible flow past a NACA 0012 wing profile, for a range of angles of attack, from low lift through stall. A stabilized finite element method is used, referred to as General Galerkin (G2), with adaptive mesh refinement with respect to the error in target output, such as aerodynamic forces. Computational predictions of aerodynamic forces are validated against experimental data.
Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2012. , 13 p.
, TRITA-CTL-4, 023
IdentifiersURN: urn:nbn:se:kth:diva-95389OAI: oai:DiVA.org:kth-95389DiVA: diva2:528062
FunderSwedish e‐Science Research Center
QC 201209132012-05-232012-05-232013-04-09Bibliographically approved