Comparison of several methods of predicting the pressure loss at altitude across a baffled aircraft-engine cylinder Page: 4 of 40
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SCDf fricticn-drag coefficient of fin-baffle passage
F pressure-drop coefficient of fin-baffle passage (includes
pressure change at baffle exit and is equal to C,
when this pressure change is negligible) i
op specific heat of air at constant pressure. 0.24 Btu per
pound per OF
G cooling-air mass flow based on baffle free-flow area,
slugs per second per square foot
acceleration of gravity, 32.2 feet per second per second
H heat dissipated from cylinder to cooling air, Btu per
pound
mechanical equivalent of heat, 778 foot-pounds per Btu
K, C, m, experimental constants
n, S
t*.
L length of fin-baffle passage, feet
M Mach number
p static pressure, pounds per square foot
Q dynamic pressure, pounds per square foot
R universal gas constant
Re Reynolds number
T static air temperature, "R
Th average cylinder-head temperature, 03
Tm average cooling-air temperature in fin-baffle passage,
XT2 + T3)/2, OR
T' ratio of cooling-air stagnation temperature riso across
fin-baffle passage to static cooling-air temperature
at baffle inlet, 3t 2t T2SNACA TN No. 1067
3
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Neustein, Joseph & Schafer, Louis J., Jr. Comparison of several methods of predicting the pressure loss at altitude across a baffled aircraft-engine cylinder, report, May 1946; (https://digital.library.unt.edu/ark:/67531/metadc54907/m1/4/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.