Effect of Vibrational Excitation on the Theoretical Performance of the Stoichiometric Carbon-Oxygen Propellant System
- Creators
- Schroeder, J. H.
Abstract
Accurate calculations to evaluate the performance of the stoichiometric carbon-oxygen propellant system have been carried out for nozzle flow with and without chemical reactions and with and without vibrational adjustment. The calculations show that, for frozen chemical flow, a lag of vibrational energy states at chamber conditions nearly doubles the reduction in I_(sp), as compared with flow in which complete vibrational equilibrium is maintained. On the other hand, lags in vibrational adjustment have practically no effect on the theoretical performance of hot propellant systems if chemical equilibrium is maintained during nozzle flow. The preceding conclusions are in agreement with the results on other propellant systems obtained previously by use of an approximate evaluation procedure.
Additional Information
(Reprinted from Journal of the American Rocket Society, January-February 1953) Copyright, 1953, by the American Rocket Society, Inc., and reprinted by permission of the copyright owner. Received August 15, 1952. This paper is based on a thesis submitted to the graduate school of the California Institute of Technology, in partial fulfillment of requirements for the degree of Aeronautical Engineer, June 1952. The author is indebted to Dr. S. S. Penner for helpful suggestions throughout the course of the work.Attached Files
Reprint - 31_Schroeder_JH_1953.pdf
Files
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Additional details
- Eprint ID
- 16974
- Resolver ID
- CaltechAUTHORS:20091214-134536542
- Created
-
2009-12-14Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center
- Other Numbering System Name
- Guggenheim Jet Propulsion Center
- Other Numbering System Identifier
- 31