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Titolo:
AEROELASTIC COMPUTATIONS ON WING-BODY-CONTROL CONFIGURATIONS ON PARALLEL COMPUTERS
Autore:
BYUN C; GURUSWAMY GP;
Indirizzi:
NASA,AMES RES CTR,MCAT INST,APPL COMPUTAT AERODYNAM BRANCH MOFFETT FIELD CA 94035
Titolo Testata:
Journal of aircraft
fascicolo: 2, volume: 35, anno: 1998,
pagine: 288 - 294
SICI:
0021-8669(1998)35:2<288:ACOWCO>2.0.ZU;2-C
Fonte:
ISI
Lingua:
ENG
Soggetto:
FLOWS;
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Science Citation Index Expanded
Citazioni:
19
Recensione:
Indirizzi per estratti:
Citazione:
C. Byun e G.P. Guruswamy, "AEROELASTIC COMPUTATIONS ON WING-BODY-CONTROL CONFIGURATIONS ON PARALLEL COMPUTERS", Journal of aircraft, 35(2), 1998, pp. 288-294

Abstract

A multizonal capability for aeroelastic computation of complex geometries has been implemented in ENSAERO, an aeroelastic analysis code with Euler/Navier-Stokes now solver, on the IBM SP2 parallel computer. The discipline parallelization is achieved by distributing the fluid, structure, and control domains onto different groups of computational nodes. The fluid domain is further parallelized based on the multizonal method. The coupling between the fluids and structures is obtained by exchanging the interface boundary data at every iteration by using theexplicit message passing interface standard library. The performance of the current implementation shows that about 12 computational nodes of the SP2 computer are equivalent to the speed of a single C90 processor. For demonstration purposes, static aeroelastic computations coupled with control surfaces are made for an arrow wing-body-control configuration in the transonic how regime. Computed pressure coefficients for a rigid configuration were compared with the mind-tunnel experiment. The two results show good agreement. Steady aeroelastic simulations are made with and without control surface deflections. The static aeroelastic simulations show that the effect of flexibility is significanton aerodynamic coefficients. It is noted that the flexible wing lowered the sectional lifts compared to the rigid wing. This procedure can be utilized for the fast computational solution of large-scale mind-tunnel models and real configurations that inevitably deform under aerodynamic loads.

ASDD Area Sistemi Dipartimentali e Documentali, Università di Bologna, Catalogo delle riviste ed altri periodici
Documento generato il 21/09/20 alle ore 12:57:57