Experimental Characterization of Nonlinear Damping in the F-16 Wing Structure
Author:
Affiliation:
1. U.S. Air Force SEEK EAGLE Office, Eglin Air Force Base, Florida 32542-6865
2. U.S. Air Force Research Laboratory Munitions Directorate, Eglin Air Force Base, Florida 32542-5427
Funder
Air Force Office of Scientific Research
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/am-pdf/10.2514/1.C035850
Reference13 articles.
1. Limit Cycle Oscillation Flight Test Results of a Fighter with External Stores
2. Theoretical Predictions of F-16 Fighter Limit Cycle Oscillations for Flight Flutter Testing
3. Limit-cycle oscillation studies of a fighter with external stores
4. On the nonlinear structural damping mechanism of the wing/store limit cycle oscillation
5. Store-Induced Limit Cycle Oscillations due to Nonlinear Wing-Store Attachment
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1. Toward an Efficient Method for F-16 Limit Cycle Oscillation Prediction;Journal of Aircraft;2023-10-25
2. Flutter Predictions for Very Flexible Wing Wind Tunnel Test;Journal of Aircraft;2022-07
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