Towards an Efficient Method for F-16 Limit Cycle Oscillation Prediction

Document Type


Publication Date



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.


This article is accessible by subscription via the DOI link on this page.

Current AFIT members may download the article by clicking here [html]. A PDF is available at that location.

Source Publication

Journal of Aircraft

This document is currently not available here.