Numerical Investigation of Aerofoil Cascade and Tandem Cascade Using Vortex Panel Method

Panel methods are the numerical schemes for solving linear, inviscid, irrotational flow fields about arbitrary bodies at subsonic free-stream Mach numbers. The basic procedure is to discretize the body in terms of singularity distribution on the body surface then satisfy the necessary boundary conditions. It helps to determine the resulting distribution of singularity on the surface, and there by obtaining fluid dynamic properties of the flow. This project work describes a method for simulating, the potential flow field about the arbitrary two-dimensional bodies using MATLAB program. Even though singularities can be used as sources, doublets, or vortices, at this point the panel method uses the vortex element because it is talented to model both lifting forces and pressures. The numerical codes developed for this purpose computes the circulation, flow velocities, coefficient of lift and coefficient of pressure distribution over various geometries along with the streamline of corresponding bodies. Similarly the flow analysis is done for the same two dimensional bodies using FLUENT flow simulation tool and the results have been compared. The advantages of this numerical scheme over the conventional flow analysis are also presented in terms of reliable flow field data.