High Chamber Pressure and Regenerative Cooling Test of the Mono-Propellant Isolde 120-A,
NAVAL AIR ROCKET TEST STATION LAKE DENMARK DOVER N J
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The monopropellant Isolde 120-A consists of a 33 percent solution of diisopropyl aminium nitrate salt and anhydrous nitric acid. This report presents variations in engine performance with chamber pressures up to 950 psia and characteristic lengths as low as 30 inches. It is recommended that Isolde be further tested for regenerative cooling characteristics at high chamber pressure that the monopropellant be tried in a specially-designed variable thrust engine and that methods for ignition be further refined and method of shut-down improved. The engine evaluations reported here were made for general application. Regenerative cooling of a small engine without resorting to unconventional design or sacrifice of performance is demonstrated. Variations in performance with characteristic length L and chamber pressure Pc are also shown. This data will aid in the application of Isolde 120-A.
- Rocket Engines
- Liquid Rocket Propellants