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Ignition of Liquid Fuels in Supersonic Air Streams
Interim scientific rept. 1 Dec 77-31 Oct 78
VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCEAN ENGINEERING
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An experimental study of the ignition of liquid fuels injected transverse to a hot supersonic M1.65 air stream was conducted. The liquids considered were kerosene, CS2 and water as an inert control. The major variables were air stagnation temperature in the range 1500 to 2300 F, injectant flow rate and injection angles from 90 to 45 deg upstream. The experimental observations were temperature measurements on the wall near the injector and in the flow downstream of injection, self-luminosity photographs and infrared photographs taken with a Thermographic camera. Special attention was directed at the behavior of the liquid layer that had previously been found to form near the injector. No unequivocal evidence of ignition of either fuel was found for normal injection at these conditions. However, clear evidence of ignition of CS2 was found for the upstream injection angle for T sub o or 2030 F and 80 or P sub j or 135 psi. High injection pressures and thus high flow rates failed to produce ignition at any temperature tested. Evidence of CS2 ignition was found in the infrared photographs and wall and in-stream temperature measurements simultaneously. The infrared photographs indicated possible ignition of the kerosene for upstream injection, but this could not be corroborated with the temperature measurements. Author
APPROVED FOR PUBLIC RELEASE