Generalized information storage and retrieval system capable of generating and maintaining a file, gathering statistics, sorting output, and generating final reports for output is reviewed. File generation and file maintenance programs written for the system are general purpose routines

Berg, R. F.

Holcomb, J. E.

Kelroy, E. A.

Levine, D. A.

Mee, C., III

English

NASA Technical Reports Server

September 1970	 Brief 70-10555 
NASA TECH BRIEF 
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 Clearinghouse for Federal Scientific and Technical 
Information, Springfield, Virginia 22151. equests for individual copies or question relating to the Tech Brief program may 
be directed to the Technology Utilization Division, NASA, Code UT, Washington, D.C. 20546. 
Saturn S-lI Base Environment for Flight Evaluation 
.
A computer program has been devised to furnish 
data on flight prediction and stage evaluation of a 
space vehicle. The program reduces the Saturn S-Il 
base region flight data to isothermal and cold wall 
condition and predicts instrument readings before and 
after flight. 
The flight prediction portion of the program estab-
lishes the base region thermal environment including 
the cold wall convective heating rates, adiabatic wall 
temperatures and base pressures for a specific Saturn 
S-Il stage engine gimballing time history during 
flight. Structural temperatures are evaluated by using 
cold wall convective heating rates and the adiabatic 
wall temperature. The cold wal l convective heating 
rates are combined with radiation heating rates and 
used with structural temperatures to predict the indi-
cated total heat flux during flight. These analytical 
predictions are based on semi-empirical correlations 
which are based in turn on the 1/25 scale model test 
data without turbo-pump exhaust. For flight evalua-
tion, the indicated flight heating rates are reduced to 
isothermal and cold wall conditions and the flight data 
is made appropriate for nominal J-2 engine combustion 
pressures. 
The base region is instrumented with asymptotic 
type total heating rate calorimeter transducers in-
stalled in an isothermal wall. Because the thermal 
boundary layer is altered by the transducer presence, 
the heating values indicated by the instrument cannot
be used directly. Correlations have been derived to 
correct the heat transfer coefficient over the calorime-
ter sensor for temperature mismatch effects. These 
effects are important when the flow is parallel to the 
transducers, but not if the flow is normal to the trans-
ducers. 
Notes: 
I. This program is written in FORTRAN IV for use on 
the IBM-7094 computer. 
2. This program can be used in flight evaluation of 
the Saturn S- Il stage vehicle or adapted to future 
vehicles. It may be used for any five-engined stage 
with center engine fixed. 
3. Inquiries should be.made to: 
COSMIC 
Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: B70-10555 
Patent status: 
Inquiries about obtaining rights for the commercial 
use of this invention may be made to NASA, Code GP, 
Washington, D.C. 20546.
Source: F. D. Georgatsos of

North American Rockwell Corp.

under contract to

Marshall Space Flight Center
(MFS-16597) 
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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