Study of supersonic combustion ramjet (scramjet) and its mode of combustion involving fuel jet diffusing into supersonic oxidizing stream; simplified model, based on Newtonian flow concepts, for prediction of injectant path, and penetration distance for secondary liquid injection into supersonic stream, is presented; over 100 experiments were performed for water injection into Mach 3 supersonic airstream, for ranges of initial injection angle (28° upstream to 31° downstream), injector diameters (0.014 to 0.035 in.), and injectant total pressures (65 to 365 psia); simplicity of theory and accuracy with which it agrees with experiments appears to favor its use.
Secondary liquid injection into supersonic airstream
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 8
1966
5 pages
Article (Journal)
English
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