Gurus: Im a newbie owner of Designfoil (Dreesecode) which uses the snack program to generate lift & drag coefficients etc for airfoils. Im wondering if this program or similar airfoil simulators can be used to input a fuselage profile coordinates as though it were an airfoil & determine lift, drag & moment parameters. I realize that meaningful information is probably asking too much because of many limitations, the equivalent 'span' is so short (fuse width) & it varies (width taper), but can this method be qualitatively used to compare profile A vs B all other things being equal sort of thing?

Specifically, Im wondering about design variations of a high speed top wing mounted configuration where 1) the typical fuse outline meets the wing at the airfoil chord line & therefore the top surface of the wing section presents a 'bump' to the airflow 2) the wing is now placed lower in the fuse with semi blended fillets & the bump is reduced 3) lower wing position yet, the fuse top is an uninterrupted flowing line. Are the 'relative' calculated lift & drag & pitching moment signatures between options 1,2,3 reliable?