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Wind tunneling testing and analysis relating to the spinning of light aircraftIncluded is a summary of two studies related to the spinning of light aircraft. The first study was conducted to demonstrate that the aerodynamic forces and moments acting on a tail of a spinning aircraft can be obtained from static wind-tunnel tests. The second study analytically investigated spinning using a high angle-of-attack aerodynamic model derived from a static wind-tunnel data base. The validity of the aerodynamic model is shown by comparisons with rotary-balance data and forced-oscillation tests. The results of a six-degree-of-freedom analysis show that the dynamics and aerodynamics of the steep- and flat-spin modes of a modified Yankee have been properly modeled.
Document ID
Document Type
Conference Paper
Mccormick, B. W.
(Pennsylvania State University University Park, PA, United States)
Zilliac, G. G.
(NASA Ames Research Center Moffett Field, CA, United States)
Ballin, M. G.
(Rockwell International Corp. Downey, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 84-0558
Accession Number
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