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(Referência obtida automaticamente do Web of Science, por meio da informação sobre o financiamento pela FAPESP e o número do processo correspondente, incluída na publicação pelos autores.)

Investigation on Transonic Correction Methods for Unsteady Aerodynamics and Aeroelastic Analyses

Texto completo
Autor(es):
Silva, Roberto G. A. [1] ; Mello, Olympio A. F. [1] ; Azevedo, Joao Luiz F. [1] ; Chen, P. C. [2] ; Liu, D. D. [2]
Número total de Autores: 5
Afiliação do(s) autor(es):
[1] Inst Tecnol Aeronaut, Inst Aeronaut & Espaco, BR-12228903 Sao Jose Dos Campos - Brazil
[2] ZONA Technol, Scottsdale, AZ 85258 - USA
Número total de Afiliações: 2
Tipo de documento: Artigo Científico
Fonte: JOURNAL OF AIRCRAFT; v. 45, n. 6, p. 1890-1903, NOV-DEC 2008.
Citações Web of Science: 7
Resumo

This paper presents an expedient transonic correction technique to compute unsteady pressure distributions and aeroelastic stability in the transonic flow regime. The transonic correction procedure here is an improvement of the downwash weighting method proposed previously by several authors. The previous downwash weighting methods could provide pressure and/or force corrections to some extent by applying different weighting methods on the lifting-surface self-induced downwash resulting from aeroelastic structural displacements or prescribed motions. However, the resulting pressure/force solutions were often found to be inconsistent, because they all failed to include the proper transonic unsteady and out-of-phase effects. Our improved downwash correction method is a rational formulation to include proper transonic effects, as this formulation is based on a successive kernel expansion procedure established in accord with the formal pressure-downwash relation. Accordingly, the developed transonic correction procedure is a proper and rational one that is expected to yield more consistent aeroelastic solutions. This procedure is now a fully developed program, known as the transonic weighting aerodynamic influence coefficient procedure in the ZAERO software system, or ZTAW. Computed results by ZTAW for the unsteady pressures and aeroelastic stability boundaries for four selected wing planforms (AGARD 445.6, F-5, LANN, Lessing wings) are found to be in good agreement with measured data. In contrast to the computational-fluid-dynamics-based methods of computational aeroelasticity, the present procedure is proven to be far more computationally efficient and industrially viable while yielding comparable aeroelastic solutions. (AU)

Processo FAPESP: 04/16064-9 - Mecânica dos fluídos não estacionária: aplicações em aeronáutica e em reologia
Beneficiário:José Alberto Cuminato
Linha de fomento: Auxílio à Pesquisa - Temático
Processo FAPESP: 00/13768-4 - Aplicações avançadas de mecânica dos fluidos computacional para aeronaves de alto desempenho
Beneficiário:João Luiz Filgueiras de Azevedo
Linha de fomento: Auxílio à Pesquisa - Parceria para Inovação Tecnológica - PITE