Aerodynamic analysis of an iced airfoil at medium/high Reynolds number

The flowfield of the NLF-0414 airfoil with a prescribed ice shape is characterized with numerical solutions to the Navier--Stokes equations. Three flow solvers are used: ZEN, a code developed at CIRA, FLUENT, a commercially available code, and CFL3D, a NASA developed solver. For each code two turbulence models are selected: the Spalart--Allmaras and the shear stress transport [kappa]--[omega] model. An effort is devoted to ascertain the degree of uncertainty among the numerical codes and turbulence models. Integrated forces and pressure coefficient distributions are compared among the analytic solutions and with available experimental data. The conditions include a range of incidence angles covering pre- and poststall for a freestream Mach number and a Reynolds number of 0.21 and 4.6 x [10.sup.6], respectively. Generally, steady-state solutions are obtained; however, unsteady solutions are acquired for the highest angles of attack.