Modeling the Effects of Underwing Missile Canards on F-16 Limit Cycle Oscillations
Author:
Affiliation:
1. U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433
2. Department of Aeronautics & Astronautics, U.S. Air Force Institute of Technology, Wright–Patterson Air Force Base, Ohio 45433
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.C033301
Reference22 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. Transonic Flutter Simulations Using an Implicit Aeroelastic Solver
4. Nonlinear mechanisms of transonic aeroelastic instability for the F-16
5. Simulation of transonic limit cycle oscillations using a CFD time-marching method
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1. Toward an Efficient Method for F-16 Limit Cycle Oscillation Prediction;Journal of Aircraft;2023-10-25
2. Shock migration on an oscillating straked delta wing using an unsteady Euler solver;Journal of Fluids and Structures;2023-10
3. Experimental Characterization of Nonlinear Dynamics for F-16 Substructures;58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference;2017-01-05
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