Differences between revisions 3 and 4

Allen/Eggers Hypersonic Drag, 1957

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

-  ⇤ ← Revision 3 as of 2016-12-12 00:03:44 → 
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  Editor: KeithLofstrom
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+   ← Revision 4 as of 2016-12-12 00:43:26 → ⇥
  Size: 1471
  Editor: KeithLofstrom
  Comment:
-Deletions are marked like this.
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-Eq 23: $ T_r = T \left( 1 + { { \gamma-1 } \over 2 } M^2 \right) \approx { \gamma-1 } \over 2 } M^2 T $
+Eq 23: $ T_r = T \left( 1 + { { \gamma-1 } \over 2 } M^2 \right) \approx { { \gamma-1 } \over 2 } M^2 T $

Diff for "DragAllenEggers1957"