Towards an Efficient Method for F-16 Limit Cycle Oscillation Prediction
This study presents the development and validation of a computationally efficient prediction framework for the well-known nonlinear F-16 Limit Cycle Oscillations (LCO) phenomenon. The framework relies on a simple physical working model which has been suggested and demonstrated in the past according to which LCO is primarily a flutter instability that is bounded by the existence of nonlinear structural damping, although potentially affected by nonlinear aerodynamic effects as well. In the framework developed herein, the nonlinear structural damping (NSD) model is derived and calibrated using a novel method which simplifies the process and allows applicability of the derived NSD models for multiple aircraft download cases. Good LCO prediction capabilities are obtained using the suggested method in terms of LCO levels and trends with flight conditions, as demonstrated using four F-16 test configurations. This framework also allows several practical benefits which makes it particularly suitable for industrial-level applications.
Journal of Aircraft
Kariv, D., Kunz, D.L., and Iovnovich, M., “Towards an Efficient Method for F-16 Limit Cycle Oscillation Prediction,” Journal of Aircraft, published online October 25, 2023. [in advance of print issue]