Accession Number : ADA261648


Title :   Application of the Saha Equation to High Temperature ( or = 6000K) Rocket Exhaust


Descriptive Note : Final rept.


Corporate Author : PHILLIPS LAB EDWARDS AFB CA


Personal Author(s) : Nachtrieb, Robert T


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a261648.pdf


Report Date : Nov 1992


Pagination or Media Count : 142


Abstract : Using the Saha equations and spectroscopic constants, the computer program in this report calculates the species populations of diatomic molecules, neutrals, ions, and electrons in a plasma. The code considers the equilibrium of a two-element, chemically reacting plasma, by calculating the partition function for each species. By rederiving theoretically, as the JANAF tables do, the thermodynamic properties of a rocket propellant, but using extended excitation levels, the program can estimate (above 6000 K) performance of advanced propulsion concepts.


Descriptors :   *SUBROUTINES , *ROCKET EXHAUST , INPUT , IONS , COMPUTATIONS , CHEMICAL DISSOCIATION , SPACE EXPLORATION , APPLIED MATHEMATICS , CARBON DIOXIDE , PLASMAS(PHYSICS) , NITROGEN , FORTRAN


Subject Categories : Computer Programming and Software
      Combustion and Ignition


Distribution Statement : APPROVED FOR PUBLIC RELEASE