Slater, Mervin O. (1949) Calculation of enthalpy-entropy diagrams for rocket propellant systems. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-12242008-124334
The purpose of this thesis is to present a method and the fundamental data necessary to construct enthalpy-entropy diagrams and from these diagrams to calculate theoretical performance of rocket motor propellants. The systems investigated using this method are:
(1) RFNA-Ammonia (1) (2) Ammonia (1)-Ozone (1) (3) Hydrogen (1) Ozone (1)
Enthalpy-entropy diagrams for these fuels were constructed for several different mixture ratios: over oxidized, stoichiometric, and under-oxidized. Performance was calculated assuming chamber pressures of 600 psia and 300 psia and exhaust pressures of 14.7 psia, 7.35 psia, and 0.147 psia. These diagrams facilitate the investigation of the effect of varying chamber pressure on chamber temperature and performance. They also facilitate investigation of varying expansion ratio, varying mixtures ratios, etc. They are especially useful in determining the performance of step rockets where exhaust conditions may vary from sea level to vacuum.
The results of the performance calculations indicate that performance found by using enthalpy-entropy diagrams checks closely with those determined by other methods. The performance of the last two systems is such as to indicate that a more thorough study of them should be made.
|Item Type:||Thesis (Engineer's thesis)|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 June 1948|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||15 Jan 2009|
|Last Modified:||26 Dec 2012 03:15|
- Final Version
See Usage Policy.
Repository Staff Only: item control page