Numerical simulation: Supersonic flow around wing-body configuration with integrated engine nacelle

Masahiro Kanazaki; Shigeru Obayashi; Kazuhiro Nakahashi

doi:10.2514/2.1963

Numerical simulation: Supersonic flow around wing-body configuration with integrated engine nacelle

Masahiro Kanazaki, Shigeru Obayashi, Kazuhiro Nakahashi

Creative Flow Research Division

Research output: Contribution to journal › Article › peer-review

3 Citations (Scopus)

Abstract

A numerical simulation of flowfields around a supersonic transport aircraft with integrated engine nacelles is presented. In this study, flowfields were simulated by solving the Euler equations with the unstructured grid method for handling the complex geometry. To simulate intake flows at actual flight conditions, a throat was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated in detail by changing throat heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results showed excellent agreement with wind-tunnel data obtained at the National Aerospace Laboratory of Japan.

Original language	English
Pages (from-to)	213-217
Number of pages	5
Journal	AIAA journal
Volume	41
Issue number	2
DOIs	https://doi.org/10.2514/2.1963
Publication status	Published - 2003 Feb

ASJC Scopus subject areas

Aerospace Engineering

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10.2514/2.1963

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title = "Numerical simulation: Supersonic flow around wing-body configuration with integrated engine nacelle",

abstract = "A numerical simulation of flowfields around a supersonic transport aircraft with integrated engine nacelles is presented. In this study, flowfields were simulated by solving the Euler equations with the unstructured grid method for handling the complex geometry. To simulate intake flows at actual flight conditions, a throat was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated in detail by changing throat heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results showed excellent agreement with wind-tunnel data obtained at the National Aerospace Laboratory of Japan.",

author = "Masahiro Kanazaki and Shigeru Obayashi and Kazuhiro Nakahashi",

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AU - Kanazaki, Masahiro

AU - Obayashi, Shigeru

AU - Nakahashi, Kazuhiro

PY - 2003/2

Y1 - 2003/2

N2 - A numerical simulation of flowfields around a supersonic transport aircraft with integrated engine nacelles is presented. In this study, flowfields were simulated by solving the Euler equations with the unstructured grid method for handling the complex geometry. To simulate intake flows at actual flight conditions, a throat was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated in detail by changing throat heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results showed excellent agreement with wind-tunnel data obtained at the National Aerospace Laboratory of Japan.

AB - A numerical simulation of flowfields around a supersonic transport aircraft with integrated engine nacelles is presented. In this study, flowfields were simulated by solving the Euler equations with the unstructured grid method for handling the complex geometry. To simulate intake flows at actual flight conditions, a throat was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated in detail by changing throat heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results showed excellent agreement with wind-tunnel data obtained at the National Aerospace Laboratory of Japan.

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Numerical simulation: Supersonic flow around wing-body configuration with integrated engine nacelle

Abstract

ASJC Scopus subject areas

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