Linear theory is used, without two dimensional or slender body assumptions, to predict flow field produced by aircraft wing, nose, inlet, and pylons. Aircraft shock wave locations are predicted, and their effect on flow field is included through transformation of aircraft geometry. Program was written in FORTRAN IV for CDC 6400 computer

Fernandes, F.

Fox, C. H., Jr.

English

NASA Technical Reports Server

June 1973 
•	 NASA TECH BRIEF S	
Langley Research Center 
B73-10183 
E-NNA 
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.C. 20546. 
Theoretical Prediction of Interference Loading on Aircraft Stores: 
Part II - Supersonic Speeds 
The problem:	 Notes: 
Accurate prediction of interference loads on pylon- 	 1. This program was written in FORTRAN IV for the 
mounted aircraft stores.	 CDC-6400 computer. 
2. Reference: Theoretical Prediction of Interface Load-
The solution:	 ing of Aircraft Stores, Part I - Subsonic Speeds, 
A program was developed for theoretically pre- 	 NASA Tech Brief B73-10184. 
dicting the loading on pylon-mounted stores in super- 	 3. Inquiries concerning this program should be directed 
sonic flow,	 to:
COSMIC 
112 Barrow Hall 
University of Georgia 
Athens, Georgia 30601 
Reference: LAR-1 1250 
How it's done: 
Linear theory is used, without two dimensional or 
101	 produced 
body assumptions, to predict the flow field 
by the aircraft wing, nose, inlet, and pylons. 
Aircraft shock wave locations are predicted, and their 
effect on the flow field is included through a trans-
formation of the aircraft geometry. The interference 
loading is integrated over the store length by considering 
the local crossflow, its axial and radial derivatives, and 
buoyancy. Store moment calculations under an F-4 
aircraft at Mach 1.2 are compared to wind tunnel data. 
The method is computerized, and program user infor-
mation is included. A companion Tech Brief (see notes) 
discusses a similar program for subsonic speeds.
Source: Charles H. Fox 
Langley Research Center and
F. Fernandes of
General Dynamics 
under contract to

Langley Research Center 
(LAR-1 1250) 
Category 06, 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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Theoretical prediction of interference loading on aircraft stores: Part II - Supersonic speeds

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