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

Masahiro Kanazaki, Shigeru Obayashi, Kazuhiro Nakahashi

Research output: Contribution to journalArticlepeer-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 languageEnglish
Pages (from-to)213-217
Number of pages5
JournalAIAA journal
Volume41
Issue number2
DOIs
Publication statusPublished - 2003 Feb

ASJC Scopus subject areas

  • Aerospace Engineering

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