Supersonic Flow Over Moderate Aspect Ratio Wings
6.10.1 Symmetric Problem
The fundamental solution is a supersonic source and the solution of the linearized small disturbance equation is given by 
where в = Jm0 – 1.
The source strength is determined by imposing the surface boundary condition. Hence
q(x, y) = U — (x, y) (6.134)
The domain of integration E is the part of the (x, y)-plane intercepted by the upstream Mach cone from the field point (x, y, z).
The pressure coefficient is, as before
2 дф p U dx
It can be shown that, for an infinite wing, the surface pressure coefficient, according to the above formula, is
(x – O
– в2[(y – n)2 + z2]
c = 2 dl = 1 де
p в dx в dx
which is consistent with the thin airfoil theory in Chap. 3.