Development of a Method to Predict Transonic Limit Cycle OscillationCharacteristics of Fighter Aircraft (October 1990)

摘要

An analysis of steady wind tunnel data, obtained for a fighter type aircraft, hasindicated that shock-induced and trailing-edge separation plays a dominant role in the development of Limit Cycle Oscillations (LCO) at transonic speeds. On this basis, a semi-empirical LCO prediction method is being developed which makes use of such steady wind tunnel data. The preliminary method has been applied to several configurations and has correctly identified those which have encountered LCO. The method has the potential for application early in the design process of new aircraft to determine and understand these non-linear aeroelastic characteristics.