Pressure Distribution on an Aerofoil 1

[cmato]

I have recently been told on an answer to a previous question I posted on this forum of a way to find an approximation for the critical (or stall) angle of an aerofoil using pressure distribution techniques. I have taken many measurements on an aerofoil to find pressure differences at different points on this aerofoil section and I am quite pleased with the results. For the different values above the aerofoil I calculated a mean value and did the same with the values for the under-side. The difference in pressure (from top and bottom sides) was found and from this an approximation of a stall angle was estimated.

I was wondering if anyone could tell me if this was the correct procedure, as I can't help wondering if I should have taken only one value on each side of the aerofoil instead.

Many thanks.
Chris
cmaitland_uk@yahoo.com