An airfoil section in a wind tunnel has many static taps on its upper and lower surface. These static ports can only read static pressure which acts perpendicularly to the local airfoil surface.
In place A are static ports that read a pressure value of relative -100 Pa . This pressure acts perpendicularly to the airfoil surface, so it is not perpendicular x co-ordinate. Do we need to convert only this vertical component when we put this value in a diagram when we draw the pressure distribution? The pressure in place A has a vertical component (lift) and also a horizontal component (thrust) .... So how would the integral "know" in which direction the pressure acts?
Can you please explain with an example from start (pressure measurement) to end (calculated forces) how this procedure looks like? (Are the experimentally measured pressures at static ports given in relative or absolute pressure?)
Angle theta is different for every place at airfoil surface, so it cant be one theta from leading edge to trailing edge. Where is here function that describe airfoil top and bottom contours? That function will give us local surface inclination