Rough supercruise numbers

I have done some calculations to find supercruise mach numbers of various fighter aircraft. My resultant numbers seem way wrong, but I’ll let the rest of you pick apart my quick calculations.:)

First for a quick derivation:
At mach mach number, flight is steady, Thrust=Drag.
Drag, FD=1/2*rho*S*CD*v^2=1/2*rho*S*CD*gamma*R*T*M^2
Thrust, FT=FD
Therefore FT=1/2*rho*S*CD*gamma*R*T*M^2, and we combine the constants to:
FT=k*M^2
This should hold for max overall speed (at full afterburner), and at max dry thrust.
Therefore
FTwet=k*Mwet^2
-> k=FTwet/Mwet^2
-> FTdry=FTwet/Mwet^2*Mdry^2
-> Mdry=Mwet*sqrt(FTdry/Ftwet)
Mdry is our supercruise (or more correctly max dry thrust mach number) mach number, and this seems like a pretty sane quick and dirty back of the envelope calculation. So here are my results for various fighter aircraft

Forces are in kN. For aircraft with multiple engines, I only used values for single engine, as the factor of 2 cancels anyway.

Sea Level:
Mwet FTdry FTwet Mdry
F-15(220 engine) 1.2 77.62 111.2 1.0
F-16(F110-100) 1.2 76.3 128.9 0.92
EF Typhoon 1.2 60 90 0.97

Altitude:
Su-27 2.35 74.5 122.6 1.83 (no.)
F-35 1.67 125 191 1.35 (prolly a bit high)
EF Typhoon 2.0 60 90 1.63 (prolly a bit high)
F-22 2.25 113 156 1.91 (prolly a bit high)

The main issue is probably ensuring that engine thrust figures match the altitude of Mwet. This is probably what threw my numbers out of whack. Thoughts?