Problem 2:
The definition of the pressure coefficient on an airfoil surface is
Then, we have the formula
C₁ = P P₂
0.5 pV:
C₁ = 1- V/V₂Y.
Based the data in the figure below, you do the following questions:
/VY as a function of x / c
(a) Plot C₂ = 1-
(b). Estimate the lift coefficient C, on the upper surface by approximately integrating
the area in the C-plot.
(c) Estimate the pitching moment coefficient C, on the upper surface relative to the
leading edge based on the C, -plot. Note that the nose-up pitching moment is is
positive.