Design of an airfoil leading edge slat using an inverse aerodynamic calculations method

Voorstel voor een studieontwerp van een achterklep voor een profiel met behulp van rekenmethoden

Application of a constrained inverse method in the aerodynamic design of a low speed wing-slat configuration

At NLR a system for the computational design on multi-element airfoil has been developed. This design system solves the inverse aerodynamic problem in an approximate way. A priori specified aerodynamic requirements (surface pressure distribution) and geometric requirements are minimized in a least-squares way, introducing weight factors to...