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

Masahiro Kanazaki, Shigeru Obayashi, Kazuhiro Nakahashi

研究成果: Paper査読

抄録

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.

本文言語English
DOI
出版ステータスPublished - 2002
イベント40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
継続期間: 2002 1 142002 1 17

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period02/1/1402/1/17

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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