Simulation of airflow past a 2D NACA0015 airfoil using an isogeometric incompressible NavierStokes solver with the SpalartAllmaras turbulence model
Isogeometric finite element NavierStokes solver based on Chorin projection. RANS turbulence modeling with the SpalartAllmaras turbulence model. High Reynolds number flow (Re=2.5106 R e = 2.5  10 6 ) around a 2D NACA0015 airfoil. Reasonable experimental agreement for computed lift, drag and pressure coefficients. Increasing the element order from p=1 p = 1 to p=2,3 p = 2 , 3 does not improve the results.
naca0015 airfoil spalartallmaras isogeometric analysis chorin projection method