Technique for Optimizing the Aerodynamic Design of a Generalized Combat Aircraft with Forward Swept Wings for the Purposes of Stability and Control Investigation

摘要

A technique was developed to optimize the airframe for aerodynamic performance of a genaralized combat aircraft with a forward swept wing with close coupled canard. A computer program was written and its output includes geometric and other parameters as a required for stability and control studies. A second computer program was written to estimate the aerodynamic stability and control derivatives of an optimized airframe. Two airframes with a single engine and with two engines were investigated. The flying qualities problems arising from the configurations were studied. An analogue simulation was carried out which highlighted some problems resulting from the longitudinal static instability inherent in both configurations. A trade off between the requirement for minimum weight and the stability characteristics is undertaken.