Jane-DoH, as I wrote in previous post, these equations can only be applied for subsonic speeds to get an exact answer. I guess we could use them to answer your example with some kind of correcting factor ''q'' as the aerodynamic heating at M 2.0 is still low. But then we would be assuming laminar isentropic flow for supersonic airspeeds which is quite wrong, however as i said, we should end up with an answer close to what we would have if we used the correct (quite complex) equations for super/hypersonic speeds..
So what do we know, M=2.0 and SAT=220 Kelvin
TAT - SAT = 1/2 M^2 (γ-1) SAT q
(a reasonable value for q at M 2.0 would be i think 3-5%, q= 1.03-1.05)
TAT - SAT = 0.5*4*(1.4 - 1)*220*1.05
TAT - SAT = 184.6 degrees of Ramrise
TAT= 184.6 + SAT = 404.6 K = 131 Celsius, would be heating up the leading edges of the aircraft..
Hope this helps
Jetpipe.