Implicit unstructured Navier-Sokes simulation of leading edge separation over a pitching airfoil (Q1294477)

We simulate the two-dimensional laminar flow over a pitching airfoil by using an implicit unstructured grid Navier-Stokes algorithm. The inviscid and viscous fluxes are represented using second-order accurate discretizations employing Roe's method and Gauss' theorem, respectively. The temporal integration is an implicit first-order backward Euler differencing. The linear system arising from the discretization for the governing equations is solved using preconditioned BI-CGSTAB, with incomplete factorization of the Jacobian used as the preconditioning matrix. We present computations for NACA0012 airfoil pitching about the quarter-chord at a freestream Mach number \(M_\infty=0.2\) and Reynolds numbers \(\text{Re}_c=10^4\) and \(2\times 10^4\) at a dimensionless pitching rate \(\Omega^+_0=0.2\).