An analysis of steady wind tunnel data, obtained for a fighter type aircraft, has indicated that shock-induced and trailing-edge separation play a dominant role in the development of Limit Cycle Oscillations (LCO) at transonic speeds. On the basis of these data a semi-empirical LCO prediction method was developed. Its preliminary version has been applied to several configurations and has correctly identified those which have encountered LCO. It has already shown the potential for application early in the design process of new aircraft to determine and understand the non-linear aeroelastic characteristics. In the present paper this method is upgraded on the basis of results of unsteady wind tunnel force and pressure measurements obtained from on oscillating fighter type wings.
Outline and Applications of a Semi-Empirical Method for Predicting Transonic Limit Cycle Oscillation Characteristics of Fighter Aircraft
1995
24 pages
Report
Keine Angabe
Englisch
British Library Conference Proceedings | 1995
|British Library Online Contents | 1992
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