Computer program utilizes a desired gas sidewall temperature profile as an input and calculates the coolant passage dimensions required to achieve it. Second program utilizes fixed coolant passage dimensions as an input and calculates the resulting temperature profile

Derderian, G.

Duscha, R. A.

Rohde, J. E.

English

NASA Technical Reports Server

December 1971	 Brief 71-10508 
NASA TECH BRIEF 
Lewis Research Center. 
NASA Tech Briefs announce new 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. f. 20546. 
I	 11111111M 
Design and Evaluation of Con'ectielv Cooled Nozzle,,
 
The problem: 
To devise a method of designing the coolant 
passages of a convectively cooled nozzle such that 
the design would be compatible with the overall 
structure and the nozzle operation would remain 
within acceptable stress limits. 
The solution: 
Two digital computer programs for the design 
and evaluation of the nozzle coolant passages. The 
programs perform the necessary calculations for the 
final design of a convectively cooled nozzle operating 
at steady-state conditions. 
How it's done: 
The first program utilizes a desired gas sidewall 
temperature profile as an input and calculates the 
coolant passage dimensions required to achieve it. 
The second program utilizes fixed coolant passage 
dimensions as an input and calculates the resulting 
temperature profile. Both programs are usually used 
to arrive at a design; the first program to obtain 
approximate coolant passage dimensions, and the 
second to check the resulting wall temperatures for a 
practical set of coolant passage dimensions. The 
resulting wall temperatures and pressures are used to 
determine the magnitude of the tangential and longi-
tudinal stresses in the coolant passage walls. The 
second program may also be used for evaluating 
existing designs; that is, for calculating wall tempera-
tures of a given coolant passage design for any set 
of coolant flow conditions. 
The programs are set up to utilize a library sub-
routine of hydrogen properties, a range of heat 
transfer correlations, and different tube surface rough-
ness conditions. 
Notes: 
1. This program is written in FORTRAN IV for use 
on the IBM-7094 computer. 
2. Requests for further information may be directed 
to:
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: B71-10508 
Patent status: 
No patent action is contemplated by NASA. 
Source: J.E. Rohde, R.A. Duscha, and

G. Derderian
Lewis Research Center

(LEW- 10894) 
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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Design and evaluation of convectively cooled nozzles

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