Record Details

Record 1 of 1
Forced Oscillation Wind Tunnel Testing for FASER Flight Research Aircraft
NTRS Full-Text: Click to View  [PDF Size: 1.2 MB]
Author and Affiliation:
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)
Abstract: As 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
Publication Date: Aug 13, 2012
Document ID:
20120014506
(Acquired Oct 15, 2012)
Subject Category: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number: NF1676L-14053
Document Type: Conference Paper
Meeting Information: 2012 AIAA Atmospheric Flight Mechanics Conference; 13-16 Aug. 2012; Minneapolis, MN; United States
Meeting Sponsor: American Inst. of Aeronautics and Astronautics; Reston, VA, United States
Contract/Grant/Task Num: WBS 747797.02.09.20.04
Financial Sponsor: NASA Langley Research Center; Hampton, VA, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 12p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: WIND TUNNEL TESTS; RESEARCH AIRCRAFT; FLIGHT TESTS; FLIGHT ENVELOPES; LOW SPEED WIND TUNNELS; FREE FLIGHT; PILOTLESS AIRCRAFT; AERODYNAMIC FORCES; DAMPING; OSCILLATIONS; ANGLE OF ATTACK; SIDESLIP; YAW; ROLLING MOMENTS; NONLINEARITY; DEGREES OF FREEDOM; STATIC TESTS
› Back to Top
Facebook icon, External Link to NASA STI page on Facebook Twitter icon, External Link to NASA STI on Twitter YouTube icon, External Link to NASA STI Channel on YouTube RSS icon, External Link to New NASA STI RSS Feed
Find Similar Records
 
NASA Logo, External Link

NASA Official: Gerald Steeman
Sponsored By: NASA Scientific and Technical Information Program
Site Curator: STI Support Services
Last Modified: April 09, 2013

Privacy Policy & Important Notices Disclaimers, Copyright, Terms of Use Freedom of Information Act USA.gov NASA.gov NASA OCIO Free Adobe PDF Reader Free MS Word Viewer