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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.
eng-tips forums is member supported.
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:

2009-09-05, 10:13 PM	#1
huangyhg 超级版主注册日期: 04-03 帖子: 18592 精华: 36 现金: 249466 标准币资产: 1080358888 标准币	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. eng-tips forums is member supported. 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: __________________ 借用达朗贝尔的名言：前进吧，你会得到信心! [url="http://www.dimcax.com"]几何尺寸与公差标准[/url]