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|  MIL-P-85662(AS)
The propellant flame temperature is computed
4.3.4 Flame temperature.
from the formula:
where
T = propellant flame temperature, 0K
Yi = constituent weight, percent
Ei and Ci are constants as shown below.
Ci
Ei
Constituent
0.3424
275.45
13.10% N
Nitrocellulose
276.98
0.3423
13.11% N
0.3421
283.10
13.15% N
13.20% N
0.3418
290.25
293.81
13.22% N
0.3417
13.23% N
0.3416
295.30
13.25% N
0.3415
296.87
0.3438
952.00
Nitroglycerine
0.3210
-668.00
Dinitrotoluene
-3009.00
0.3471
Diphenylamine
-1552.00
0.6403
Water
-2785.00
0.4879
Ethyl acetate
-800.00
0.1250
Calcium carbonate
-800.00
0.1250
Sodium sulfate
-3224.00
0.1349
Graphite
0.2158
-24.9
Potassium nitrate
0.0421
-111.00
Tin oxide
-2656.00
0.4258
Dibutyl phthalate
10
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