Abstract
The paper presents a Reynolds-averaged Navier-Stokes (RANS) computational aeroelastic investigation of the Limit Cycle Oscillations (LCO) phenomenon of the F16 aircraft wing, with correlation to flight tests. The study is the first step towards a new computational capability, currently under development, to enable the prediction of the LCO phenomenon for Israeli Air Force purposes. The study presents aeroelastic simulations of the full-span F-16 fighter computational model including a detailed linear modal structural model and an aerodynamic wing model. The simulations are performed at flow conditions for which LCO was encountered in flight tests. The effects of dynamic pressure, structural damping, angle of attack and turbulence modeling on the characteristics of the phenomenon are discussed. The relationship between flutter and LCO is investigated, and the origin of LCO is identified as a nonlinear, self-sustained, periodic, shock-wave oscillations on the upper surface of the wing. These oscillations are suggested to suppress flutter into LCO.
| Original language | English |
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| State | Published - 2015 |
| Event | 16th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2015 - Saint Petersburg, Russian Federation Duration: 28 Jun 2015 → 2 Jul 2015 |
Conference
| Conference | 16th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2015 |
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| Country/Territory | Russian Federation |
| City | Saint Petersburg |
| Period | 28/06/15 → 2/07/15 |
All Science Journal Classification (ASJC) codes
- Mechanical Engineering
- Aerospace Engineering