Digital computer program computes and analyzes supersonic flow field in axisymmetric rocket nozzle for specified gas properties, nozzle geometry, and input or starting line. Method of characteristics is used for solution of set of hyperbolic partial differential equations

Elliott, J. J.

Stromsta, R. R.

English

NASA Technical Reports Server

November 1970	 Brief 70-10597 
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WA.
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- -- - 
Digital Program Analyzes Supersonic Flow Field

Within Bell-Shaped Rocket Nozzles 
A digital computer program was written and devel-
oped for computing and analyzing the supersonic- flow 
field within an axisym metric, bell-shaped rocket nozzle 
for specified gas properties, nozzle geometry, and in-
put or starting line. 
This program determines the flow parameters 
throughout the nozzle for an ideal gas with a specified 
specific heat ratio y; or for a reacting gas composition 
(frozen or shifting) for which the dynamic and thermo-
dynamic properties are tabulated functions of Mach 
number. The program uses the axisymmetric method 
of characteristics for steady, irrotational, supersonic 
flow, and computes the wall pressure profile, nozzle 
thrust coefficient, and vacuum thrust efficiency. 
The method of characteristics is used for the solu-
tion of a set of hyperbolic partial differential equa-
tions in steady supersonic, axisymmetric flow. The 
vector equationsmay be written which express con-
tinuity of flow, the potential or energy of flow, and 
irrotationality of flow. These vector equations (ap-
proximately 71) are used in this program, and may be 
expanded to a Set of hyperbolic partial differential 
equations describing flow in the supersonic flow field. 
The partial differential equations can be further re-
duced to yield the total differential equations for the 
characteristic surfaces throughout the flow field. 
Notes: 
I. This program is written in FORTRAN 11 for the 
IBM 360 computer. 
2. Inquiries may be made to: 
COSMIC 
Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: B70-10597 
Source: J. J. Elliott and R. R. Stromsta of

North American Rockwell Corp.

under contract to

Marshall Space Flight Center

(M FS- 14292) 
Category 09 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned -rights.
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Digital program analyzes supersonic flow field within bell-shaped rocket nozzles

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