aeroheating
aeroheating
(OP)
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.
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.





RE: aeroheating
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.
RE: aeroheating
STF
RE: aeroheating
http://naca.larc.nasa.gov/cit.html
or
http://ntrs.nasa.gov/
for articles about super and hypersonic flight
TTFN