Digital computer program considers an unswept wing with a circular or elliptical fuselage. Wing has partial or full span deflected flaps and must have an aspect ratio of 6 or greater

Fox, C. H.

Kisielowski, E.

Mc Veigh, M. A.

English

NASA Technical Reports Server

December 1971
	 Brief 71-10501 
NASA TECH BRIEF 
Langley Research Center
	
_4V 
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 aubscription 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. 
Prediction of Stall Characteristics of Straight Wing Aircraft 
The solution: 
A digital computer program which considers an
	 2. 
iinswept wing with a circular or elliptical fuselage. 
The wing may have partial or full span deflected 
flaps and must have an aspect ratio of 6 or greater. 
The problem: 
To calculate the spanwise distributions of lift, drag, 
and pitching moment coefficients on a wing-fuselage 
combination up to the angle-of-attack at which stall 
occurs, and to predict the spanwise position of ini-
tial stall. 
How its done: 
For a wing without fuselage, Sivells' lifting-line 
method (NACA TR 1090) is employed. When a 
fuselage is present, Multhopp's method (NACA TM 
1036) is used to transform the wing-fuselage combi-
nation into an equivalent wing-alone configuration. 
Lifting-line theory is then applied to this transformed 
configuration. The theory employs two-dimensional, 
experimental airfoil characteristics to obtain the lift, 
drag, and pitching moment coefficients at each sta-
tion on the wing span. 
The program determines the wing spanwise lift 
distribution by an iterative procedure. Once this 
distribution is established, the distributions of drag 
and pitching moment are obtained from the curves 
of experimental two-dimensional airfoil section 
characteristics. Spanwise integration of the lift, drag, 
and pitching moment distributions yields the over-
all wing lift, drag, and pitching moment, respectively. 
If calculations are made at a sufficiently high 
value of fuselage angle-of-attack, a spanwise section 
will reach a point equal to the angle-of-attack for 
maximum lift, as determined from the two-dimen-
sional section data. When this occurs, the wing is
said to stall. Thus the method can be used to de-
termine the point of initial stall on the wings of 
wing-fuselage combinations. 
Notes: 
I. This program is written in FORTRAN IV for 
use on a CDC-6600, version 2.3, with a Scope 
3.0 operating system and library tape. 
The following documentation may be obtained 
from: 
National Technical Information Service 
Springfield, Virginia 22151 
Single document price $3.00 
(or microfiche $0.95) 
Reference: 
NASA CR-1646 (N71-31154), A Design 
Summary of Stall Characteristics of 
Straight Wing Aircraft 
3. Requests for further information on the program 
may be directed to: 
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: B71-10501 
Patent status: 
No patent action is contemplated by NASA. 
Source: C.H. Fox

Langley Research Center, and

M.A. McVeigh and

E. Kisielowski of

Dynasciences Corp.

under contract to
Langley Research Center

(LA R-110 13) 
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.
https://ntrs.nasa.gov/search.jsp?R=19710000498 2020-03-17T02:26:21+00:00Z


Prediction of stall characteristics of straight wing aircraft

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