Consider a thin airfoil of unit chord length placed in a Mach 2 supersonic freestream parallel to the x-axis. The airfoi

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Consider a thin airfoil of unit chord length placed in a Mach 2
supersonic freestream parallel to the x-axis. The airfoil leading
edge is at x=0. The trailing edge is at x= 1. The lower surface of
the airfoil is flat, lying on the x-axis.
The upper surface is made of a parabolic arc: Z(x) = 0.04 * x *
(1 – x)
Compute and sketch Cp vs x/c using Ackert's theory. Compute Cl ,
Cd and the pitching moment coefficient at the leading edge Cm,LE
using Ackert's theory. Compute also the center of pressure. Show
all the work. Do not use a calculator for integration.