I was wondering if anyone knows of an equation that will properly calculate the rate of heating on any material, at any altitude, at any speed, and with air hitting that surface at any angle.(adsbygoogle = window.adsbygoogle || []).push({});

The equation will be somewhere similar to

(DT/dt)t=0=(Tr-Tinitial)h/(cρz)

Where:

T=temperature

t=time

Tr=T0(1+0.2rM^2) where r=recovery factor~0.84 for laminar air flow~0.89 for

turbulent air flow

Tinitial=initial temperature

h=kNNu/x

k=3.58E-6[717/(T0+225)](T0/492)^3/2

NNu=0.0271Re^0.8

x=boundary layer distance from the nose

Re=ρVL/μ

ρ=density of fluid

V=mean fluid velocity

L=travel length of fluid

μ=the dynamic viscosity of the fluid

c=specific heat

z=thickness

However, this equation is for (specifically) heating on a thin rocket airframe.

Any help would be greatly appreciated.

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# Rate of Heating on an angle

Can you offer guidance or do you also need help?

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