Supersonic natural laminar flow wing

摘要

A reverse delta aerodynamic wing has a basic reverse delta wing portion bounded by a leading edge and by a pair of trailing edges extending from respective ends of said leading edge toward a trailing apex point and respective span-wise wing extensions in a natural laminar boundary layer wing region extending chordwise from said leading edge by a fraction of the chordlength of said wing and extending span-wise from opposing sides of said wing. Laminar flow control in other regions of the wing employs fuel stored in the wing as a coolant.