Investigation of missile control surface effects on F-16 limit-cycle oscillation
Document Type
Article
Publication Date
3-2015
Abstract
Tactical aircraft with thin wings and heavy external wing stores are susceptible to aeroelastic limit-cycle oscillations. This investigation applies both frequency-domain and time-domain solutions using aeroelastic computational models to predict limit-cycle oscillation onset, frequency, and amplitude on an F-16. The test configuration uses missile shapes with reconfigurable aerodynamic and mass properties. Statistical analysis of flight-test results identifies significant experimental variables of missile aerodynamic configuration, flight condition, and aircraft fuel state. Furthermore, statistical analysis permits the normalization of flight-test results for direct comparison to aeroelastic models. Results of the comparison show that flight-test data analysis mostly supports the prediction trends, but the magnitude of the aerodynamic effects due to the canards and fins is much less significant in the test data.
Source Publication
Journal of Aircraft (ISSN 0021-8669 | eISSN 1533-3868)
Recommended Citation
Hanson, C. Q., Kunz, D. L., & Lindsley, N. J. (2015). Investigation of missile control surface effects on F-16 limit-cycle oscillation. Journal of Aircraft, 52(2), 462–470. https://doi.org/10.2514/1.C032741
Comments
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