KNSU Characteristics

[DiegoParedesE]

I saw a previous request to include KNSU in default propellants. Mod asked for characteristics. The following characteristics were sourced from Richard Nakka's Experimental Rocketry Web Site.

	Parameter		Units	Note
	Process method	Cast
Isp	Specific Impulse, ideal	166	sec.	1
Isp	Specific Impulse, delivered (typical)	130	sec.	2
C*	Characteristic exhaust velocity, theoretical	3106	ft/s
To	Combustion temperature, theoretical @1000 psia	1447 (1720)	deg Celsius (K)	3
To	Combustion temperature, measured@1000 psia	1350	deg Celsius	4
ρ'	Density, ideal	1.89	gram/cu.cm.
ρ	Density, as cast (typical)	1.80	gram/cu.cm.	5
ρ'/ ρ	Density ratio	0.95
X	Mass fraction of condensed-phase products	0.424	-
k	Ratio of specific heats, 2-phase flow	1.044	-	6
k	Ratio of specific heats, static	1.133	-	7
M	Effective molecular wt. of exhaust products	41.98	g/mole	8

Notes:

1. At 1000 psi pressure; exit pressure one atmosphere
2. Static tests AST-17, AST-18
3. PROPEP combustion results
4. Measured with type k thermocouple, static test AST-16
5. Measured (liquid displacement method), typical grain for B-200 motor
6. Effective (2-phase), at chamber conditions
7. Value for exhaust mixture
8. System mass divided by number of gas moles

Burn rate behavior	Burn rate behaviour	de St.Robert		Note
n	Burn rate pressure exponent, strand	0.319
n	Burn rate pressure exponent, erosive	0.323
a	Burnrate constant	0.0665		1
ro	Burn rate @ 1 atm.	0.156	in/sec
r	Burn rate @ 1000 psia	0.602	in/sec
Tcr	Auto-ignition temperature	> 300	deg. C.

1. Use with pressure units of psi. Resulting burn rate is inches per second

Chamber Pressure v.s. Kn

[reilleya]

Great, looks like everything needed is here. Thanks!

[reilleya]

Done