Serdengecti, S. (1991) A Procedure for Predicting Fuel Specific Impulse of Supersonic Combustion Ramjet Engines. California Institute of Technology , Pasadena, CA. (Unpublished) https://resolver.caltech.edu/CaltechAUTHORS:20141114-112342961
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Abstract
This report presents a procedure in order to portray the effect of design choices on SCRAMJET dynamic performance in the context of real gas effects. Procedure is based on one-dimensional fluid flow analysis. The less quantifiable aspects of boundary layer transition, mixing, and non-uniform nozzle flow are included in approximate parametric fashion by allowing for parallel flow paths through the engine and nozzle, with possibility of thermal energy exchange between various flow streams. The effect of finite recombination rates in the nozzle is included by allowing for freezing of the chemical composition at any specified static pressure in the nozzle. Exploratory results from the digital implementation of this procedure in FORTRAN language are also included.
| Item Type: | Report or Paper (Technical Report) | ||||
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| Additional Information: | © 1991 California Institute of technology. This work, in part, was financially support by Daniel and Florence Guggenheim Jet Propulsion Center, California Institute of Technology, Pasadena, CA. | ||||
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| Record Number: | CaltechAUTHORS:20141114-112342961 | ||||
| Persistent URL: | https://resolver.caltech.edu/CaltechAUTHORS:20141114-112342961 | ||||
| Usage Policy: | No commercial reproduction, distribution, display or performance rights in this work are provided. | ||||
| ID Code: | 51774 | ||||
| Collection: | CaltechAUTHORS | ||||
| Deposited By: | INVALID USER | ||||
| Deposited On: | 14 Nov 2014 22:02 | ||||
| Last Modified: | 03 Oct 2019 07:36 |
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