Propellant Spray Combustion Processes During Stable and Unstable Liquid Rocket Combustion

Abstract

Information resulting from this study will allow formulation of new and very general analytical models and criteria to permit a priori design of reliable and stable liquid rocket motors and supersonic air-breathing engines required for future weapons delivery systems. From the test data drop diameterso, velocity and pressure wave growth or decay as a function nf chamber length and initial conditions will be determined. These data can then be input to appropriate newly deyeloped combustion models and the validity of the coupling term expressions evaluated by directly comparing the resulting predictions to experimental data.vi R-8377 ACKNOWLEDGMENT