Numerical simulation of supersonic flow around wing-body configuration with integrated engine nacelle

Masahiro Kanazaki; Shigeru Obayashi; Kazuhiro Nakahashi

doi:10.2514/6.2002-836

Numerical simulation of supersonic flow around wing-body configuration with integrated engine nacelle

Masahiro Kanazaki, Shigeru Obayashi, Kazuhiro Nakahashi

Creative Flow Research Division

Research output: Contribution to conference › Paper › peer-review

Abstract

This paper presents numerical simulation of flowfields around a supersonic transport aircraft with an integrated engine nacelle. 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 flights, a bump was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated hi detail by changing bump heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results were compared with wind tunnel data obtained at National Aerospace Laboratory of Japan.

Original language	English
DOIs	https://doi.org/10.2514/6.2002-836
Publication status	Published - 2002
Event	40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 2002 Jan 14 → 2002 Jan 17

Other

Other	40th AIAA Aerospace Sciences Meeting and Exhibit 2002
Country	United States
City	Reno, NV
Period	02/1/14 → 02/1/17

ASJC Scopus subject areas

Space and Planetary Science
Aerospace Engineering

Access to Document

10.2514/6.2002-836

Fingerprint Dive into the research topics of 'Numerical simulation of supersonic flow around wing-body configuration with integrated engine nacelle'. Together they form a unique fingerprint.

Cite this

@conference{f3916eddcde04ae8b3f7ee6d5ef25c68,

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

abstract = "This paper presents numerical simulation of flowfields around a supersonic transport aircraft with an integrated engine nacelle. 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 flights, a bump was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated hi detail by changing bump heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results were compared with wind tunnel data obtained at National Aerospace Laboratory of Japan.",

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

year = "2002",

doi = "10.2514/6.2002-836",

language = "English",

note = "40th AIAA Aerospace Sciences Meeting and Exhibit 2002 ; Conference date: 14-01-2002 Through 17-01-2002",

}

TY - CONF

T1 - Numerical simulation of supersonic flow around wing-body configuration with integrated engine nacelle

AU - Kanazaki, Masahiro

AU - Obayashi, Shigeru

AU - Nakahashi, Kazuhiro

PY - 2002

Y1 - 2002

N2 - This paper presents numerical simulation of flowfields around a supersonic transport aircraft with an integrated engine nacelle. 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 flights, a bump was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated hi detail by changing bump heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results were compared with wind tunnel data obtained at National Aerospace Laboratory of Japan.

AB - This paper presents numerical simulation of flowfields around a supersonic transport aircraft with an integrated engine nacelle. 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 flights, a bump was introduced inside the nacelle. The effect of nacelle mass flow ratios on overall aerodynamic performance was investigated hi detail by changing bump heights. The spillage drag was calculated and found to have a large impact on the total drag. Computed results were compared with wind tunnel data obtained at National Aerospace Laboratory of Japan.

UR - http://www.scopus.com/inward/record.url?scp=85088758755&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85088758755&partnerID=8YFLogxK

U2 - 10.2514/6.2002-836

DO - 10.2514/6.2002-836

M3 - Paper

AN - SCOPUS:85088758755

T2 - 40th AIAA Aerospace Sciences Meeting and Exhibit 2002

Y2 - 14 January 2002 through 17 January 2002

ER -

Numerical simulation of supersonic flow around wing-body configuration with integrated engine nacelle

Abstract

Other

ASJC Scopus subject areas

Access to Document

Other files and links

Cite this