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Forced Oscillation Wind Tunnel Testing for FASER Flight Research AircraftAs unmanned air vehicles (UAVs) continue to expand their flight envelopes into areas of high angular rate and high angle of attack, modeling the complex unsteady aerodynamics for simulation in these regimes has become more difficult using traditional methods. The goal of this experiment was to improve the current six degree-of-freedom aerodynamic model of a small UAV by replacing the analytically derived damping derivatives with experimentally derived values. The UAV is named the Free-flying Aircraft for Sub-scale Experimental Research, FASER, and was tested in the NASA Langley Research Center 12- Foot Low-Speed Tunnel. The forced oscillation wind tunnel test technique was used to measure damping in the roll and yaw axes. By imparting a variety of sinusoidal motions, the effects of non-dimensional angular rate and reduced frequency were examined over a large range of angle of attack and side-slip combinations. Tests were performed at angles of attack from -5 to 40 degrees, sideslip angles of -30 to 30 degrees, oscillation amplitudes from 5 to 30 degrees, and reduced frequencies from 0.010 to 0.133. Additionally, the effect of aileron or elevator deflection on the damping coefficients was examined. Comparisons are made of two different data reduction methods used to obtain the damping derivatives. The results show that the damping derivatives are mainly a function of angle of attack and have dependence on the non-dimensional rate and reduced frequency only in the stall/post-stall regime
Document ID
20120014506
Document Type
Conference Paper
Authors
Hoe, Garrison (NASA Langley Research Center Hampton, VA, United States)
Owens, Donald B. (NASA Langley Research Center Hampton, VA, United States)
Denham, Casey (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 26, 2013
Publication Date
August 13, 2012
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NF1676L-14053
Meeting Information
2012 AIAA Atmospheric Flight Mechanics Conference(Minneapolis, MN)
Funding Number(s)
WBS: WBS 747797.02.09.20.04
Distribution Limits
Public
Copyright
Public Use Permitted.

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