Computational Investigation of the Compressible Dynamic Stall Characteristics ofthe Sikorsky SSC-A09 Airfoil

摘要

Steady and unsteady two-dimensional flowfield analysis was conducted for aSikorsky SSC-AO9 airfoil in compressible, high Reynolds number flows. Limited verification with experimental measurement was achieved. Computational methods included a steady, linear panel method with compressibility corrections; a laminar and turbulent boundary layer method; an unsteady, linear panel method; and a numerical solution method of the thin layer, compressible, Navier-Stokes equations using a body-fitted C-type computational grid. The Baldwin-Lomax, two-layer, zero-equation turbulence model was used. Wind tunnel wall interference effects were ignored. Steady and unsteady airloads and instantaneous flow pictures are presented. In steady flow with little or no separation, computed lift, drag, pitching moment, and skin friction coefficients, as well as displacement thickness and boundary layer velocity profiles at several angles-of-attack were generally found to be in good agreement with experimental data.