Preliminary Results from the Unsteady Airfoil Model USTAR2,
TEXAS TECH UNIV LUBBOCK
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Preliminary results from an UnSTeady AiRfoil analysis in 2 dimensions have been obtained from a computer code USTAR2 developed by the present authors. This computer code is based upon an analysis which uses a doublet panel method to model the airfoil surface, an integral unsteady boundary layer scheme to model the viscous attached flow, and discrete vortices to model the detached boundary layers which form the airfoil wake region. This model has been used successfully to predict steady lift and drag coefficients as well as pressure distributions for several airfoils with both attached and detached boundary layers. In addition, calculations have been made for a limited number of cases for both attached and detached unsteady flow situations. These calculations are compared in a cursory way with experimental data to point out some of the strengths and weaknesses of the present formulation.