Effect of canard oscillations on the vortical flowfield of a X-31A-like fighter aircraft model
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Authors
Liu, Da-Ming
Subjects
High angle of attack aerodynamic
Effect of pitch rate and canard oscillations vortex breakdown
Flow visualization by dye injection
X-31A-like fighter aircraft model
Effect of pitch rate and canard oscillations vortex breakdown
Flow visualization by dye injection
X-31A-like fighter aircraft model
Advisors
Hebbar, S.K.
Platzer, Max F.
Date of Issue
1992-03
Date
March 1992
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
A flow visualization investigation was carried out in the Naval Postgraduate School water tunnel using the dye injection technique to study the effects of oscillating a close-couple canard on a 2.3% scale model of a X-31A-like fighter aircraft. This investigation focused primarily on the effects of canard oscillations on the breakdown characteristics of the wing root vortex for both static and dynamic conditions of the model at zero slideslip angle. The main result of the first of a kind water tunnel visualization data suggest that for the static conditions of the model the low frequency/high frequency canard oscillations tend to destabilize/augment wing vector core, I.e., promote/delay bursting of the wing vortex. The dynamic tests indicate that the large amplitude low frequency oscillations of the canard react favorably with the wing vortical flowfield to delay vortex bursting during both pitch-up and pitch-down motions.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics and Astronautics
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funder
Format
120 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
Copyright is reserved by the copyright owner.