Computer program calculates the inviscid one-dimensional equilibrium, frozen, and nonequilibrium nozzle expansion of gaseous propellant exhaust mixtures containing the elements - carbon, hydrogen, oxygen, nitrogen, fluorine and chlorine. The program performs calculations for conical nozzles only

Frey, H. M.

Kliegel, J. R.

English

NASA Technical Reports Server

October 1968	 Brief 68-10375 
.	
NASA TECH BRIEF 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
One-Dimensional Reacting Gas Nonequilibrium Performance Program 
The problem: 
To develop a one-dimensional method for calcu-
lating the equilibrium, frozen, and kinetic perfor-
mance of propellant systems having gaseous exhaust 
products containing the elements: carbon, hydrogen, 
oxygen, nitrogen, fluorine, and chlorine. 
The solution: 
A computer program which calculates the inviscid 
one-dimensional equilibrium, frozen, and nonequi-
librium nozzle expansion of gaseous propellant exhaust 
mixtures containing the six elements. 
How it's done: 
The program considers the 19 significant gaseous 
species present in the exhaust mixtures of propellants 
containing the above elements and the 48 chemical 
reactions (1 3 dissociation—recombination reactions 
and 35 binary exchange reactions) which can occur 
between the exhaust products. In order to reduce 
computation time per case to a minimum, the pro-
gram uses a second order implicit integration method. 
This integration method has been demonstrated to 
reduce the computation time per case several orders 
of magnitude when directly compared with the com-
putation times required using standard explicit meth-
ods such as fourth order Runge—Kutta or Adams—
Moulton methods. 
The program is completely self-contained, requir-
ing specification of only the propellant system (ele-
mental composition and heat of formation), relaxation 
rates, and nozzle geometry to run a case. The chemi-
cal species considered have been selected to allow 
accurate equilibrium, frozen, and kinetic perform-
ance analyses of cryogenic, space storable, prepack-
aged, hybrid, and solid propellant systems of current 
and projected operational use. This program allows 
analysis of the performance loss associated with film 
cooling in propellant systems having all gaseous ex-
haust products. It also allows simultaneous consid-
eration of both chemical and gas-particle relaxation 
losses in propellant systems having condensed exhaust 
products. The program is designed for engineering 
use and is specified and programmed in a straight-
forward mnner to facilitate its use as a development 
tool. 
Notes: 
1. The program is written in Fortran IV for use 
on the IBM 7094 computer. 
2. This program will perform calculations for coni-
cal nozzles only. 
3. Related computer programs are described in 
NASA Tech Briefs 68-10374, 68-10376, and 
68-10377. 
4. Inquiries concerning the program may be directed 
to:
COSMIC 
Computer Center 
University of Georgia 
Athens, Georgia 30601 
Reference: B68-10375 
Patent status: 
No patent action is contemplated by NASA. 
Source: J. R. Kliegel and H. M. Frey 
of TRW Systems 
under contract to 
Manned Spacecraft Center 
(MSC-1 1777) 
Category 06 
This document was prepared under the sponsorship of the National	 Government assumes any liability resulting from the use of the 
Aeronautics and Space Administration. Neither the United States 	 information contained in this document, or warrants that such use 
Government nor any person acting on behalf of the United States	 will be free from privately owned rights.
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One-dimensional reacting gas nonequilibrium performance program

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