XFOIL: an analysis and design system for low Reynolds number airfoils.

Abstract

Presents calculation procedures for viscous/inviscid analysis and mixed inverse design of subcritical aerofoils. Demonstrates an inviscid linear vorticity panel method with a Karman/Tsien compressibility correction for direct and mixed inverse modes. The effect of the viscous layer is modelled by source distribution superimposed on the aerofoil and wake. A two equation lagged dissipation integral method is used to represent the viscous layers. An e9 type amplification is used in determination of the transition point. The boundary layer and transition equations are solved simultaneously with the inviscid flowfield by a global Newton method. Shows example calculations for low Reynolds number aerofoil flows with transitional separation bubbles. Calculated surface pressure distributions and polars are compared with experimental data. (from author's abstract)