Solid Propellant Test Evaluation of Water-Cooled Nozzle
Final rept. 15 Oct 1967-1 Mar 1969
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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The objective of this test program was to evaluate the feasibility of using a water-cooled nozzle on large solid propellant motors. The coolant requirement for this test was 1200 galmin water flow rate with an inlet coolant pressure of 850 psi. The flow was reduced during the test with a minimum water flow rate of 560 galmin. The nozzle performed successfully with no indication of tube burnthrough or film boiling occurring. Test duration was 62 seconds at an average chamber pressure of 380 psi. Results of this test indicated the entire system operated satisfactorily at maximum operating conditions.
- Combustion and Ignition
- Rocket Engines
- Solid Propellant Rocket Engines