Jetpipe
Jane-DoH, as I wrote in previous post, these equations can only be applied for subsonic speeds to get an exact answer.
I did not know that
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.
Where do you derive "q" from?
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..
Understood. What formula is that out of curiousity?