How to derive 3D Lift and Drag Coefficients of a Rectangular Wing Sail from 2D Airfoil Profile Section

Iam currently working on modeling of wing sail for ship, which is same a a rectangular wing with a unifrom airfoil cross section. Is there a package or a code to convert the 2D cl, cd versus alpha of the correpsonding airfoil to be converted to the 3D CL,CD , alpha distribtuion after considering the effects of tip vortex and induced drag. I need to do this for post stall as well.

Answer 1

[Anshuman]

There are few packages to convert 2D airfoil data to 3D wing data. One option is to use a computational fluid dynamics (CFD) software package, such as ANSYS Fluent or OpenFOAM, to perform the 3D analysis. CFD software can simulate the flow around a 3D wing and calculate the lift and drag coefficients, including the effects of tip vertices and induced drag.

There are other tools like XFOIL/XFLR5 also. XFOIL has the capability to calculate the 2D lift and drag coefficients of an airfoil as a function of angle of attack (alpha), and it can also calculate the 3D lift and drag coefficients of a wing using the lifting-line theory.

For post-stall analysis, you may need to use a more advanced method, such as a vortex lattice method or a panel method, to account for the complex flow behavior that occurs at high angles of attack. These methods are available in some CFD software packages.

[Mohammed]

Is there any way in Matlab to do this conversation