Multipoint Aerodynamical Shape Optimization of Flying Configurations with Spanwise Movable Leading Edge Flaps, in Supersonic Flow



The multipoint aerodynamical shape optimization of a flying configuration (FC) is realized by morphing. Spanwise movable leading edge flaps are used. It leads to two enlarged variational problems, with free boundaries. The own developed iterative optimum-optimorum theory, which searches the global optimized shape inside an elitary class of flying configurations (FCs) and new hybrid solutions for the compressible full Navier-Stokes PDEs, are used. (© 2012 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)