What happens to the centre of pressure?
Hi all, im in a spot of bother here with a discussion point on a lab report.
What happens to the centre of pressure on a symmetric aerofoil before and after stall?
As far as I know, the centre of pressure is roughly at the 1/4 chord in normal flight and moves backwards with increasing angle of attack? what happens after the stall? does it go to the trailing edge? and how would i tell this by looking at a table of pressure coefficients for different points on a wing at varying angles of attack?
could someone please answer in simple to understand terms?