blackmail
JD,
it might be the formula of Raleigh for supersonic speeds :
Pt-p/p =[ 166,92158M^7/(7M^2-1)^2,5]
-1
Pt = Total Air Pressure
p = Static Air Pressure
M^7 = Mach to the power 7
M^2 = Mach to the power 2(square)
^2,5 = power 2,5
And this gives you the "q-factor" or does it give you the stagnation temperature? I don't see any temperature figures in there...
BTW: How do you determine total air-pressure? Can I just set it as an "x-value" and then fill in the rest, then solve for it?