Unsteady inviscid flowfields of 2D airfoils by non-linear singular integral computational analysis

A two-dimensional aerodynamics representation analysis is introduced for the investigation of inviscid flowfields of unsteady airfoils. The problem of the unsteady flow of a two-dimensional NACA airfoil is therefore reduced to the solution of a non-linear multidimensional singular integral equation, when the form of the source and vortex strength distribution is dependent on the history of the above distribution on the NACA airfoil surface. An application is given to the determination of the velocity and pressure coefficient field around an aircraft by assuming constant source distribution.

▶ Non-linear multidimensional singular integral equation for 2D unsteady aerodynamics. ▶ Determination of the velocity and pressure coefficient field around an aircraft. ▶ Turbulent boundary layer model based on the behavior of the momentum integral equation. ▶ General type of the source and vortex strength distribution around the NACA airfoils. ▶ Unsteady momentum integral equation for both laminar and turbulent flows.