Differences between revisions 4 and 5

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 4 as of 2016-12-12 00:43:26 → 
  Size: 1471
  Editor: KeithLofstrom
  Comment:
+   ← Revision 5 as of 2016-12-12 00:44:00 → ⇥
  Size: 1473
  Editor: KeithLofstrom
  Comment:
-Deletions are marked like this.
+Additions are marked like this.
 Line 23:
-Eq 25: $ ( T_r - T_W) = V^2 / 2 C_p $ ... since $ V_{sound} = \sqrt{ ( \gamma - 1 ) C_p T $ . at altitude
+Eq 25: $ ( T_r - T_W) = V^2 / 2 C_p $ ... since $ V_{sound} = \sqrt{ ( \gamma - 1 ) C_p T } $ . at altitude

Diff for "DragAllenEggers1957"