The calculation of the two dimensional viscous incompressible flow about
single and multielement aerofoil sections is considered.
A panel method, based on vorticity and source distributions is used for
the calculation of the potential flow. Once the velocity distribution is
known, integral boundary layer methods are employed to predict the viscous
effects. A wake model has also been developed for the calculation of the wake
behind the aerofoil system.
The solution is iterative. At the end of each iteration the velocities
on the aerofoil are corrected for viscosity and wake effects; the wake position
is also relaxed, before the next iteration starts.
The mathematical model of the flow, together with the computer program
written to test the model are described here in detail. The numerical results
obtained using the computer program are found to be in good agreement with
both experimental data and exact solutions.
A Masters Dissertation, submitted in partial fulfilment of the requirements of the award of Master of Science of Loughborough University.