A correction factor for pressure distribution analysis of an aerofoil in a subsonic flow

الملخص EN

This study investigates the gِِeometrical solution for a given pressure (i.e.

velocity) distribution of subsonic flow around an aerofoil section using an analytical method.

The results show that the analytical method is not precise on the leading edge, when it is used to solve the mean camber line of updated profile RAE (Royal Aircraft Establishment).

Therefore, a correction parameter with changeable values ranging between 0.32 and 0.42 was created, and it gives appropriate results.