Allen/Eggers Hypersonic Drag, 1957

In METRIC!


Symbols:

$ T_r

Kelvins

Recovery temperature

T_w

Kelvins

Wall temperature

T

Kelvins

Temperature at altitude

M

-

Mach number at altitude

H

J / m2

Heat transferred per unit area

h_l

J / m2 - K

Heat transfer coefficient

C_v

J / kg K

Specific heat capacity at constant volume

C_p

J / kg K

Specific heat capacity at constant pressure

gamma

C_p / C_v

Specific heat capacity ratio, typically 1.4

Assuming that the Prandtl number is unity.

Eq 23: T_r = T \left( 1 + { { \gamma-1 } \over 2 } M^2 \right) \approx { \gamma-1 } \over 2 } M^2 T

Eq 25: ( T_r - T_W) = V^2 / 2 C_p ... since V_{sound} = \sqrt{ ( \gamma - 1 ) C_p T . at altitude

Heat transfer coefficient h_l

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