Potential Flow over a NACA Four-Digit Airfoil

Streamlines and the surface pressure coefficient are plotted for potential flow over some members of the NACA four-digit family of airfoils. Each plot includes values for the lift coefficient and pitching moment coefficient about the leading edge. Camber and thickness of the airfoil are controlled by varying digits of the identification number. Controls are also available to digitize the airfoil for the numerical computation, and for the angle of attack the airfoil makes with the uniform onset flow. A panel method using straight-line vortex panels of linearly varying strength and external Neumann boundary conditions provides the numerical solution to the modelComponente Curricular::Educação Superior::Ciências Exata