Theoretical Considerations

• The flow over the airfoil is assumed to be steady incompressible and irrotational.

• The governing flow equation is ?2?=0, Laplace’s equation of the velocity potential.

• The boundary condition is

• The solution of the flow is obtained by steady first order panel method. The FORTRAN code, AIGE is written.

• The effect of the ground is obtained by mirror image method such that v=0 on the ground surface.

• The midpoints of the panels are chosen as the control points.

Previous slide

Next slide

Back to first slide

View graphic version