Injection, Atomization, Ignition and Combustion of Liquid Fuels in High-Speed Air Streams.
Final rept. 1 Dec 78-30 Nov 81,
VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCEAN ENGINEERING
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Experimental studies of the penetration, break-up and atomization of transverse liquid and slurry jets were performed. All tests were with an air cross flow at Mach 3.0 with Po 4 atm. and To 300 deg K. The processes studied were 1 the effects of injectant viscosity and surface tension, 2 the performance of an impinging jet injector and 3 the effects of particle loading for a slurry jet with 3-50 micrometer particles. The diffractively scattered light method was employed at these high-density, supersonic conditions to study droplet sizes. The major results are, 1 mean droplet size is approximately 10 microns for injectors of 0.05 in., 2 it has an inverse relation with jetfree stream dynamic pressure ratio, 3 it has a direct relation with orifice diameter, 4 it decreases downstream, 5 transverse variation has no simple pattern and 6 droplet size increases with viscosity.
- Combustion and Ignition
- Liquid Rocket Propellants