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Titolo:
Flow simulation of NAL experimental supersonic airplane/booster separationusing overset unstructured grids
Autore:
Togashi, F; Nakahashi, K; Ito, Y; Iwamiya, T; Shimbo, Y;
Indirizzi:
Tohoku Univ, Dept Aeronaut & Space Engn, Sendai, Miyagi 980857901, Japan Tohoku Univ Sendai Miyagi Japan 980857901 Sendai, Miyagi 980857901, Japan Natl Aerosp Lab, Mitaka, Tokyo 1810015, Japan Natl Aerosp Lab Mitaka Tokyo Japan 1810015 , Mitaka, Tokyo 1810015, Japan
Titolo Testata:
COMPUTERS & FLUIDS
fascicolo: 6, volume: 30, anno: 2001,
pagine: 673 - 688
SICI:
0045-7930(200107)30:6<673:FSONES>2.0.ZU;2-G
Fonte:
ISI
Lingua:
ENG
Soggetto:
IMPLICIT SCHEMES;
Keywords:
overset unstructured grids; airplane/booster separation;
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Engineering, Computing & Technology
Citazioni:
11
Recensione:
Indirizzi per estratti:
Indirizzo: Togashi, F Tohoku Univ, Dept Aeronaut & Space Engn, Sendai, Miyagi 980857901, Japan Tohoku Univ Sendai Miyagi Japan 980857901 agi 980857901, Japan
Citazione:
F. Togashi et al., "Flow simulation of NAL experimental supersonic airplane/booster separationusing overset unstructured grids", COMPUT FLU, 30(6), 2001, pp. 673-688

Abstract

The overset unstructured grid method developed for multiple-body problems is applied to a flow simulation about an experimental supersonic airplane separation from a rocket booster. An unstructured grid around the rocket booster is overset on the stationary grid around the airplane and moves with time to simulate the separation process. Detailed components of the rocket booster are faithfully reproduced by the unstructured grid. This capability of the unstructured grid reduces the number of required overset grids and significantly simplifies the overset procedure. The computed result of the airplane/booster separation clearly simulates the complex reflection patterns of shock waves between two bodies during the separation process. The computed lift and pitching moment coefficients are compared with the wind tunnel results. The computational accuracy of the aerodynamic coefficients is improved by including the detailed components of the airplane and rocket. (C)2001 Elsevier Science Ltd. All rights reserved.

ASDD Area Sistemi Dipartimentali e Documentali, Università di Bologna, Catalogo delle riviste ed altri periodici
Documento generato il 28/09/20 alle ore 12:15:35