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

Masahiro Kanazaki, Shigeru Obayashi, Kazuhiro Nakahashi

Research output: Contribution to conferencePaperpeer-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 languageEnglish
DOIs
Publication statusPublished - 2002
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: 2002 Jan 142002 Jan 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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