Theoretical performance of liquid ammonia and liquid fluorine as a rocket propellant Page: 4 of 23
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6 RESTRICTED NACA RM E53A26
Specific heat at constant pressure, cal/(g)(oK)
1 0 T( A
ep p T ' ni(C) + 2 nj() Yi " P ni( A()i7)
Derivative of logarithm of pressure with respect to logarithm of density
at constant entropy
2: p1 0
YS i (a)
. T s = p -( i ) A _N
Coefficient of viscosity, poise
S PM (9)
Coefficient of thermal coInductivity, cal/(s..ec)(cm)(oK)
k = 0 eg +4-M)(10)
Then co position is assumed to be frozen, equti.ons (7) and (8)
Sp.ecific heat at constant pressre assumi n g frozen composition
frozen Ln ora (1)
D .rv.... v .. o I0. 7itCt o2 pQesC:- t. th re.:A-4-ct. to logarIthn of density
ut c. m.. ut; , s c -i c.-f on cr -osition
(g -7M'2- /0 \
S ie ) l_ v frozen
09P" L.ozen M
Thy 1 as of vrice it exit well cond uctiviy for mixtures of
co tt-stion ga.-es calculated by ir, " of questions (9) and (i0) are only
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Gordon, Sanford & Huff, Vearl N. Theoretical performance of liquid ammonia and liquid fluorine as a rocket propellant, report, July 3, 1953; (digital.library.unt.edu/ark:/67531/metadc53029/m1/4/: accessed January 21, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.