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The determination of the aerodynamical global optimized (GO) shape of a flying configuration (FC), with respect of minimum drag at cruise, leads to an enlarged variational problem with free boundaries. The proposed strategy for the determination of the GO shape of the FC is the own developed evolutionary iterative optimum-optimorum (OO) theory, which chooses the GO shape among a class of elitary FCs. In the first step of its iteration, hyperbolic analytical potential solutions are used and the inviscid GO shape of FC is deter- mined and is used as adequate surrogate FC's shape for the next step of iteration.The friction drag coefficient of the surrogate FC's shape is computed by using own developed analytical- numerical hybrid solutions for the compressible full Navier-Stokes partial-differential equ- ations and weak interactions with structure are performed. Up the second step of iteration, migrations in the drag functional, which is now the total drag (including friction) and in the constraints, including also those requested for structure purpose. Two new global optimized and fully-integrated Catamaran models are proposed for the supersonic transport aircraft and for the touristic aerospace aircraft, namely: one, which is optimized at cruising Mach number 2.2 and the second one, which is optimized at cruising Mach number 3.

GLOBAL OPTIMIZED AND FULLY- INTEGRATED SHAPE OF THE NEW GENERATION OF SUPERSONIC AIRCRAFT