Investigation of a Semi-Empirical Method to Predict Limit Cycle Oscillations ofModern Fighter Aircraft (Meeting Paper)

摘要

Requirements of modern fighter aircraft to operate with high maneuverability inthe transonic speed regime may lead under certain conditions to limit cycle oscillations (LCO), produced by a structural/aerodynamic interaction. Conditions of transonic LCO are moderate angle of attack and Mach numbers ranging from 0.9 to 1.1. An analysis of steady wind tunnel data, obtained for a fighter type aircraft in a typical configuration, has indicated that shock-induced separation plays a dominant role. In the paper, a semi-empirical prediction method is presented which makes use of these steady data, and some results are shown. Possibilities are discussed to extend the method to the use of unsteady wind tunnel data.