Computer program formulates geometric description of the wing body configuration, optimizes wing camber shape, determines wing shape for a given pressure distribution, and calculates pressures, forces, and moments on a given configuration. The program consists of geometry definition, transformation, and paneling, and aerodynamics, and flow visualization

Woodward, F. A.

English

NASA Technical Reports Server

September 1968
	 Brief 68-10335 
NASA TECH BRIEF 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
Computer Program Analyzes and Designs Supersonic Wing—Body 
Combinations 
A computer program has been designed which 
formulates a geometric description of the wing body 
configuration under study; optimizes wing camber 
shape; determines wing shape for a given pressure 
distribution; and calculates pressures, forces, and 
moments on a given configuration. 
The complete program consists of five sections: 
geometry definition, geometry transformation, 
geometry paneling, aerodynamics, and flow visualiza-
tion. 
Geometry definition defines geometrically a wing, a 
body or a wing-body combination, writing the defini-
tion on a tape that is read by the next section of the 
program. 
Geometry transformation reads the tape definitions, 
transforms the body and wing to a new coordinate sys-
tem, orients the wing planform parallel to the x-y 
plane in the transform system, and finds the inter-
sections .
 of wing percent chord lines with the body 
surface. The configurations of wing alone, body alone, 
or wing-body combination can be handled and the 
results written on tape. 
Geometry paneling does not act on the body-alone 
case. For the wing-body and wing-alone cases, this 
section combines the tape definition with the input 
data for body and/or wing cutting planes. The panel-
ing description and the additional geometric data are 
written on an output tape for printout purposes and 
on a scratch tape for use in the next section. 
Aerodynamics computes velocity components due 
to the various singularities and stores them on tape. 
Given the capability to carry out the above operation, 
the following basic types of problems can be solved: 
(l)After optimization of the wing camber surface 
shape for minimum drag with either wing lift or. 
lift and pitching moment constraints, the pressure
distribution over the wing and body and the 
associated forces and moments on the airplane are 
calculated. 
(2) The pressure distribution and forces and moments 
are obtained for a given configuration geometry 
(i.e., the solution to the direct problem). 
(3) The wing camber and twist are found to produce a 
given wing pressure distribution (i.e., the solution 
to the indirect problem). 
Flow visualization provides a method of analyzing 
the flow about the given configuration. Field velocity 
components, local flow vectors, and pressure coef -
ficients in the field are calculated and presented along 
with the streamlines. An examination of the flow at 
points on a two or three-dimensional grid, or a flow 
analysis at individual field points, can be carried out. 
Notes: 
1. This program is written in Fortran IV and MAP 
for use on the IBM 7090/94 computer. 
2. The program will be useful to anyone involved in 
aeronautical design or analysis. 
3. Inquiries concerning this program may be made 
to:
COSMIC 
Computer Center 
University of Georgia 
Athens, Georgia 30601 
Reference: B68-10335 
Patent status: 
No patent action is contemplated by NASA. 
Source F. A. Woodward 
of The Boeing Company 
under contract to 
Ames Research Center 
(ARC-10141) 
Category 06 
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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Computer program analyzes and designs supersonic wing-body combinations

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