Consider a 10 % thick bi-convex airfoil of parabolic arc upper and lower profiles with negative camber. The upper surface contributes 3 % to thickness at 50 % chord and the lower surface contributes 7...

Consider a 10 % thick bi-convex airfoil of parabolic arc upper and lower profiles with negative camber. The upper surface contributes 3 % to thickness at 50 % chord and the lower surface contributes 7 % thickness to the airfoil at mid chord. First, write the equations yu (x) and yl (x) for the upper and lower profiles. Next, use shock-expansion theory to calculate:

(a) the pressure coefficient at the leading edge, and increments of 10 % chord until trailing edge

(b) the lift coefficient

(c) the (wave) drag coefficient

(d) the pitching moment coefficient about the leading edge.