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Impact of nose-probe chines on the vortex flows about the F-16CA 1/15-scale model of the F-16C aircraft was tested at subsonic and transonic speeds to determine the effects of small nose-probe chines on the high angle-of-attack aerodynamic and stability characteristics. Off-body flow visualization using a laser vapor screen technique and six-component forces and moments were obtained at freestream Mach numbers of 0.30, 0.60, and 0.80. The nose-probe chines generated strong vortices interacting with the vortices generated over the smooth forebody or over the strakes. These vortices in turn led to global flow unsteadiness and model dynamics at the high angles of attack. The test results underscore the sensitivity of the high angle-of-attack flow field to small geometry changes in the nose region.
Document ID
19900032773
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hall, R. M.
(NASA Langley Research Center Hampton, VA, United States)
Erickson, G. E.
(NASA Langley Research Center Hampton, VA, United States)
Straka, W. A.
(George Washington University Hampton, VA, United States)
Peters, S. E.
(NASA Langley Research Center Hampton, VA, United States)
Maines, B. H.
(General Dynamics Corp. Fort Worth, TX, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-0386
Accession Number
90A19828
Distribution Limits
Public
Copyright
Other

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