Surfactants Evaluated in Static Test Motor Burns

A considerable number small rocket motor test burns using KNO₃/sorbitol (65/35)w based propellants and Polystep B-1 surfactant as a viscosity reducer have been carried out.  Several of these tests are documented at the following link under the sorbitol drop-down.  Other surfactants have also exhibited similar viscosity reduction properties to Polystep B-1.  Several of these have been used in propellant formulations and some static test motor evaluations containing them are reported on below.

Polystep B-1; ammonium nonylphenol ethoxylate sulfate, used at 0.15%

KNSO w/B-1
Burn Time = 3.52 sec
Propellant wt.  =  122.7g  =  0.270lb
Nozzle Throat area  =  0.01568 in2
Max. Thrust  =  14 lbs
Max chamber pressure   =  600 psi
Ave Thrust  =  9.2 lbs  =  40.9N
Total Impulse = 32.2 lb sec = 143.3 N sec
ISP = 119
Engine class  =  G41

Polystep B-27; sodium nonylphenol
ethoxylate sulfate, used at 0.30%

KNSO with Polystep B-27 Surfactant
Burn Time = 4.25 sec
Propellant mass = 121.6 g = 0.268 lb
Throat area = 0.01568 in2
Max Thrust = 10.0 lbs
Max Chamber Pressure = 455 psi
Ave. Thrust = 8.0 lbs = 35.6 N
Total Impulse = 151 N sec = 34 lb sec
ISP = 127
Motor Class = G36

Purex brand liquid laundry detergent;
active ingredient most likely sodium laureth sulfate, used at 1%.

KNSO w/Purex
Burn time = 3.26 sec
Propellant weight = 123.0g  =  0.271lb
Throat area  = 0.01568 in2
Max Thrust =  16.5 lbs
max pressure = 700 psi
Ave Thrust  = 9.7 lbs  =  43.2 N
Total impulse  = 31.6 lb sec  =  140.8 N sec
ISP = 117
Motor class  =  G 43