Computer program performs the many calculations necessary for solving radiating, nonadiabatic flow of air in chemical equilibrium. Solution method provides accurate description of blunt body flow field in subsonic region

Taylor, F. W.

English

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1972	 B72-10067 
NASA TECH BRIEF 
Langley Research Center 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage 
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be directed to the Technology Utilization Office, NASA, Code KT, Washington, D.C. 20546. 
Program to Determine Radiating, Nonadiabatic, Inviscid Flow Over a

Blunt Body by the Method of Integral Relations 
The problem: 
To perform the many calculations necessary for 
solving the radiating nonadiabatic flow of air in chem-
ical equilibrium. The results would describe a blunt-body 
flow field in the subsonic region. 
The solution: 
A computer program was developed in support of the 
study of the radiating, nonadiabatic, inviscid flow prop-
erties (pressure, temperature, density, velocity, and 
enthalpy) around a blunt body in equilibrium air by use 
of a modified method of integral relations. 
How it's done: 
The program calculates the radiating nonadiabatic 
flow of air in chemical equilibrium. Results obtained 
techniques. The agreement indicates that this method 
of solution provides an accurate description of the 
blunt-body flow field in the subsonic region. 
The equations which govern inviscid, radiating, non-
adiabatic steady flow of equilibrium air over a blunt 
body travelling at hypersonic speeds are a system of non-
linear partial differential equations derived from the laws 
of conservation of mass, momentum, and energy. The 
modified method of integral relations is used to trans-
form the governing equations into a set of ordinary 
differential equations that are numerically integrated to 
yield the details of the thermodynamic and flow prop-
erties within the shock layer. Provisions have been made 
in the governing equations for coupled radiating flow-
field analysis. 
The governing differential equations are solved by a 
fourth-order Runge .Kutta integration technique to give 
shock-layer thickness, shock angle, and the fluxes of 
mass, momentum, and energy at the body surface. 
The documentation contains a description of the 
computer program along with the methods used in the 
digital approximations, flow charts, instructions for the 
user, and a test case with input and output listings. 
Notes: 
1. This program is written in FORTRAN IV to be 
utilized by the CDC-6600 computer. 
2. Submitted by: Frances W. Taylor 
Langley Research Center 
Hampton, Virginia 23365 
(LAR-1 1048) 
3. Inquiries concerning this program should be directed 
to:
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601
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 free from privately owned rights.
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Program to determine radiating, nonadiabatic, inviscid flow over a blunt body by the method of integral relations

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