Optimisation of the Sekwa blended-wing-Body research UAV

Abstract

A variable stability, blended-wing-body research mini-UAV was developed at the CSIR in South Africa. The purpose of the UAV was to study some of the aerodynamic design and control issues associated with flying wing geometries and to develop a practical methodology for aerodynamic optimisation of this class of UAV. Optimisation was performed in two phases – first optimisation of the planform shape and then the design of a family of optimised aerofoils. The approach was shown to be practical and gave interesting insight into the advantages and challenges of relaxing some of the flying qualities constraints during the aerodynamic design process