Active Control Strategies to Optimize Supersonic Fuel-Air Mixing for Combustion Associated with Fully Modulated Transverse Jet in Cross Flow
Final rept. 1 May 2003-30 Sep 2005
FLORIDA INTERNATIONAL UNIV MIAMI APPLIED RESEARCH CENTER
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A 76 mm x 76 mm supersonic wind tunnel with variable Mach Numbers M 1.5 - 4 was designed and set up. The wind tunnel could support both non-reacting fuel-air mixing and combustion. A back pressure flap was added at the downstream end of the diffuser for dual mode subsonic- supersonic combustion studies. A high-speed imaging system was used for the visualization of pure liquid jet, aerated liquid jet and pulsed aerated jet injection into a supersonic cross flow at Mach number 1.5. The penetration height of the jet was determined from the average of 100 instantaneous recorded images. For the aerated jet the gas-liquid mass ratio varied from 0 to 8.2 for water and from 0 to 9.9 for methanol. For the pulsed aerated jet, the aerating gas was pulsed with a frequency range 1 - 1000 Hz at a constant duty cycle of 50 and at 1000 Hz with a variable duty cycle between 0 and 100. Results were reported in correlations.
- Combustion and Ignition