The design of a liquid propellant rocket engine thrust chamber requires the knowledge of the atomized droplet time of burning and its maximum flame sheet diameter so that the combustor length and diameter can be determined. In this work, the modified Spaldinq's analysis at supercritical pressure and temperature is presented. A computer program is coded to solve for the droplet time of burning and maximum flame sheet diameter. This code is used to solve five particular cases of those propellants which are used the most in rocket propulsion.
SARHAN, A., & EL-SENBAWI, M. (1993). SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS. International Conference on Aerospace Sciences and Aviation Technology, 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO), 111-122. doi: 10.21608/asat.1993.25611
MLA
A. M. SARHAN; M. A. EL-SENBAWI. "SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS", International Conference on Aerospace Sciences and Aviation Technology, 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, 1993, 111-122. doi: 10.21608/asat.1993.25611
HARVARD
SARHAN, A., EL-SENBAWI, M. (1993). 'SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS', International Conference on Aerospace Sciences and Aviation Technology, 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO), pp. 111-122. doi: 10.21608/asat.1993.25611
VANCOUVER
SARHAN, A., EL-SENBAWI, M. SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS. International Conference on Aerospace Sciences and Aviation Technology, 1993; 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO): 111-122. doi: 10.21608/asat.1993.25611
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