Program evaluates influences of heat transfer, stress, and cycle life. Coolant passages may be tubes or channels, with or without gas-side wall coating. Program options include two-dimensional thermal analysis model of tube or channel cross-section using relaxation technique with variable number of nodes

Gerstley, J. G.

Tobin, R. D.

English

NASA Technical Reports Server

April 1975
	 B75-10015 
•	 NASA TECH BRIEF 
Lewis Research Center 
NASA Tech Briefs announce now technology derived from the U.S. space program. They are issued to encourage 
commercial application. Tech Briefs are available on a subscription basis from the National Technical Information 
Service. Springfield, Virginia 22151. Requests for individual copies or questions relating to the Tech Brief program may 
be directed to the Technology Utilization Office, NASA. Code KT, Washington, D.C. 20546. 
Regenerative Cooling Design
and Analysis Computer Program 
^11
This computer program was written for the design and 
analysis of regeneratively cooled rocket engines; however, 
the program may be used for the design and analysis of 
any convectively cooled or heated device. 
The severe thermal environment encountered by the 
thrust chamber walls of a rocket engine necessitates some 
form of cooling. One of the more common cooling 
methods is regenerative cooling in which one of the 
working fluids, usually the fuel, is employed to con-
tinually cool the thrust chamber walls. The design of an 
efficient cooling system requires detailed evaluation of the 
hot-gas-side and coolant-side influences by calculating the 
simultaneous thermal and fluid dynamic balance incre-
mentally along the length of the structure. As with most 
cooling systems, minimum coolant pressure drop compat-
ible with acceptable wall temperature distribution is 
desirable. This computer program makes these analyses. 
The program evaluates the influences of heat transfer, 
stress and cycle life. Coolant passages may be tubes or 
channels, with or without a gas-side wall coating. Passages 
may be designed on the basis of a specified gas-side ,wall 
temperature, coolant-side wall temperature, or coating 
temperature distribution. A design may be analyzed with 
a specified coolant passage size distribution to determine 
the resulting wall temperatures and coolant pressure drop. 
Program options include a two-dimensional thermal 
analysis model of a tube or channel cross-section using a 
relaxation technique with a variable number of nodes. 
Also, a transient thermal solution is provided by a quasi 
two-dimensional thermal model for considering startup, 
shutdown and throttling influences. Another option is the 
determination of structural safety and cycle life of a 
design.
Notes: 
1. This program was written in FORTRAN IV for use on 
the IBM 360/67 computer. 
2. Inquiries concerning this program should be directed 
to:
COSMIC 
Information Services 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30602 
Reference: LEW-121 10 
Source: J.G. Gerstley and RD. Tobin

Rockwell International
under contract to
Lewis Research Center 
(LEW-121 10) 
. Category 09 
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 tree from privately owned rights.
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Regenerative cooling design and analysis computer program

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