NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Experimental study of effects of forebody geometry on high angle of attack static and dynamic stabilityA series of low speed wind tunnel tests on a generic fighter model with a cylindrical fuselage were made to investigate the effects of forebody shape on static and dynamic lateral/directional stability. Five forebodies, including a chine nose of unconventional cross-sectional shape, were tested. Conventional force tests were conducted to determine static stability characteristics and single degree-of-freedom free-to-roll tests were used to study the wing rock susceptibility of the model with the various forebodies. Flow visualization data were obtained to aid in analysis of the complex flow phenomena involved. The results show that forebody cross-sectional shape can strongly effect both static and dynamic (roll) stability at high angles of attack. Large variations in stability were obtained for the various forebody geometries. These characteristics result from the impact of cross-sectional shape on forebody vortex development, the behavior of the vortices at sideslip conditions, and their interaction with the wing and empennage flow fields.
Document ID
19860035080
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Brandon, J. M.
(NASA Langley Research Center Hampton, VA, United States)
Nguyen, L. T.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 86-0331
Accession Number
86A19818
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available