Investigation of Missile Control Surface Effects on F-16 Limit-Cycle Oscillation
Author:
Affiliation:
1. Department of Aeronautics and Astronautics, U.S. Air Force Institute of Technology, Wright–Patterson AFB, Ohio 45433
2. U.S. Air Force Research Laboratory, Wright–Patterson AFB, Ohio 45433
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.C032741
Reference23 articles.
1. Limit Cycle Oscillation Characteristics of Fighter Aircraft
2. Evaluation of classical flutter analysis for the prediction of limit cycle oscillations
3. Limit Cycle Oscillation Flight Test Results of a Fighter with External Stores
4. In-Flight Wing Deformation Characteristics During Limit Cycle Oscillations
5. Limit-cycle oscillation studies of a fighter with external stores
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1. ZEUS Application for F-16 Limit-Cycle-Oscillation Prediction;AIAA Scitech 2020 Forum;2020-01-05
2. Flight Testing at the Air Force Institute of Technology;AIAA Aviation 2019 Forum;2019-06-15
3. Aircraft Control Surface and Store Freeplay-Induced Vibrations in Aeroelastic Stability Envelope;Journal of Aircraft;2016-09
4. Visualization of Nonlinear Aerodynamic Phenomena During F-16 Limit-Cycle Oscillations;Journal of Aircraft;2016-05
5. Modeling the Effects of Underwing Missile Canards on F-16 Limit Cycle Oscillations;Journal of Aircraft;2016-01
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