aeroheating
 

aeroheating
is there any guidelines on the levels of aeroheat generated at various airspeeds?
i am interested in bodies travelling between mach 2 to mach 5 and the aeroheating that they would be subjected to. would there be any sigificant differences between the leading edges and planar surfaces.
any advice would be greatly appreciated.
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quite simple mach number calculations:
t_0/t = 1 + [(g-1)/2]*m^2
where t_0 is stagnation temperature, t is static (ambient) temperature, m is mach number, g is specific heat ratio.
g can be approximated by (n+2)/n where n is the degrees of freedom of the gas, which increases with temperature. for room temperature, diatomic conditions n=5, g=1.4. i think g~1.2 for re-entering apollo command modules.
dig around nasa's website for historical stuff about the x-15. i re
you might also simply peruse the many government lab report servers such as: