SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS
SARHAN, A., EL-SENBAWI, M. (1993). SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS. EKB Journal Management System, 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO), 111-122. doi: 10.21608/asat.1993.25611
A. M. SARHAN; M. A. EL-SENBAWI. "SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS". EKB Journal Management System, 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, 1993, 111-122. doi: 10.21608/asat.1993.25611
SARHAN, A., EL-SENBAWI, M. (1993). 'SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS', EKB Journal Management System, 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO), pp. 111-122. doi: 10.21608/asat.1993.25611
SARHAN, A., EL-SENBAWI, M. SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS. EKB Journal Management System, 1993; 5(ASAT CONFERENCE 4 - 6 May 1993, CAIRO): 111-122. doi: 10.21608/asat.1993.25611

SUPERCRITICAL DROPLET COMBUSTION: A NUMERICAL ANALYSIS

International Conference on Aerospace Sciences and Aviation Technology
Article 10, Volume 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, May 1993, Page 111-122  XML PDF (2.01 MB)
Document Type: Original Article
DOI: 10.21608/asat.1993.25611
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Authors
A. M. SARHAN1; M. A. EL-SENBAWI2
1Assistant Professor, Department of Rockets, Military Technical College, Cairo, Egypt.
2Head of Department of Rockets, Military Technical College, Cairo, Egypt.
Abstract
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.
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