Applying DLR's conceptual aircraft design system to military flying wing configurations, the design of a generic UCAV configuration is presented. For its outer shape, the SACCON geometry specified by NATO STO/AVT-161 Task Group was taken. For mission analysis and structural sizing, aerodynamic data from fast and robust conceptual design methods (i.e. potential flow theory) were used. In order to assess the validity of these simple methods for such configurations, a comparison with results from RANS aerodynamics and wind tunnel measurements was performed. The results of this design task were included into the stability and control investigations performed within the AVT-201 task group.
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