Aircraft conceptual design often focuses on unconventional
configurations like for example forward
swept wings. Assessing the characteristics
of these configurations usually requires the use
of physic based analysis modules. This is due
to the fact that for unconventional configurations
no sucient database for historic based analysis
modules is available.
Nevertheless, physic based models require a
lot of input data and their computational cost can
be high. Generating input values in a trade study
manually is work-intensive and error-prone.
Conceptual design modules can be used to
generate sucient input data for physic based
models and their results can be re-integrated into
the conceptual design phase. In this study a direct
link between a conceptual design module
and an aerodynamic design module is presented.
Geometric information is generated by the conceptual
design module and the physic based results,
in form of the Oswald factor, are then fed
back.
Apart from the direct link, an equation for determination
of the Oswald factor is derived via a
Symbolic Regression Approach
