Flowfield Near Liquid Fuel Jets Injected Transverse to a Hot Supersonic Air Stream.
VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCEAN ENGINEERING
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This paper presents the first results of a study aimed at delineating the processes leading to ignition of liquid fuel jets injected transverse to a hot supersonic air stream. The tests were conducted at Mach 1.8 with a nominal stagnation pressure of 100 psia and stagnation temperatures from 500-1800 F. Kerosene, CS2 and water were used as the injectants. The observations were in the form of direct, top-view photos, temperature measurements and top-view, infrared Thermographic photos to produce isotherm patterns. Attention was directed, in particular, at the surface layer formed on the wall near the injection port. Author
- Fluid Mechanics
- Combustion and Ignition