Accession Number : AD0918420

Title :   The Effect of Exit Velocity on the Infrared Radiation Intensity of an Exhaust Plume.

Descriptive Note : Final rept. Jun-Sep 73,

Corporate Author : AIR FORCE ARMAMENT LAB EGLIN AFB FL

Personal Author(s) : Ebeoglu, Davut B. ; Harwell, Kenneth E.

Report Date : JAN 1974

Pagination or Media Count : 20

Abstract : This report describes the results of a study of the relationship between the exhaust gas velocity and the infrared radiation emitted in the 3 to 5 micrometer band from the exhaust plume of a small rocket engine. The experimental results indicate that, for the cases of both sonic and supersonic exit nozzles, the variation in exit gas velocity has very little effect on the infrared figure of merit under static ambient conditions simulating altitude. The data also show that there is no significant correlation between thrust and infrared figure of merit. In order to make these observations, oxidizer to fuel ratios (O/F) had to be maintained to better than 5% accuracy. Otherwise, the previously described effect of O/F ratio variation is so pronounced as to completely mask the small variations due to exit gas velocity.

Descriptors :   *INFRARED RADIATION, *EXHAUST GASES, *INFRARED SIGNATURES, *PLUMES, ROCKET EXHAUST, COMPUTER PROGRAMS, ROCKET ENGINES, VELOCITY, INTENSITY, SOLID PROPELLANT ROCKET ENGINES, LIQUID PROPELLANT ROCKET ENGINES, HYBRID ROCKET ENGINES, ROCKET RAMJETS, EXHAUST NOZZLES, THERMODYNAMICS, COMBUSTION CHAMBER GASES, COMBUSTION PRODUCTS, OXIDIZERS, SLURRY FUELS, ROCKET NOZZLES, GAS DYNAMICS, RADIOMETRY, EMISSIVITY, THRUST.

Subject Categories : Infrared Detection and Detectors
      Combustion and Ignition
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE