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

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

Nastase, A.

Full Article:

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 determined 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 analyticalnumerical hybrid solutions for the compressible full Navier-Stokes partial-differential equations 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.

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 determined 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 analyticalnumerical hybrid solutions for the compressible full Navier-Stokes partial-differential equations 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.

Palavras-chave:

DOI: 10.5151/meceng-wccm2012-15490

Referências bibliográficas

• [1] Bockris, J. O Nastase A., “Computation of Supersonic Flow over Flying Configurations”. Elsevier Oxford, UK, (2007).
• [2] Nastase A., “Hybrid Navier-Stokes Solutions for Aerodynamical, Global Optimal Shape''s Design”, Proc. of Int. Conf. EngOpt, Paper 750, Rio de Janeiro, Brazil, (2008).
• [3] Nastase A., ''''Multipoint and Iterative Aerodynamical Global Shape''s Optimization''''. Proc. of Evolutionary and Deterministic Methods for Design Optimization and Control, of EUROGEN 2011, Paper 30, CIRA, Capua, Italy (2011).

Como citar:

Nastase, A.; "GLOBAL OPTIMIZED AND FULLY- INTEGRATED SHAPE OF THE NEW GENERATION OF SUPERSONIC AIRCRAFT", p-11-18. In: In Proceedings of the 10th World Congress on Computational Mechanics [= Blucher Mechanical Engineering Proceedings, v. 1, n. 1]. São Paulo: Blucher, 2014.
ISSN 23580828, DOI 10.5151/meceng-wccm2012-15490