Conclusion and Recommendations (cont’d)
Steady incompressible panel method is an easy and fast way to solve the problem.
Viscous effects in the fluid flow can not be handled.
By panel method, the effect of the ground on the lift to drag ratio can not be analysed.
The code AIGE can be coupled with a boundary layer code.
An s-shaped profile can be selected for 3-D studies.
Wing with endplates and without endplates can be compared.