Wing-tip vortex calculations using a high-accuracy scheme

David P. Lockard, Philip J. Morris

Research output: Contribution to journalArticlepeer-review

11 Scopus citations

Abstract

The objective of the research described in this paper is to investigate the use of computational aeroacoustics methodology and parallel computers to simulate the development of a tip vortex. A three-dimensional Euler code, implemented using the message passing library and Fortran 90 on the IBM SP2, is used to perform calculations of the steady flow. Results are presented for low-speed flow over a finite span NACA 0012 wing. Comparisons with experimental data show that the tip vortex is predicted to diffuse too rapidly, but the high-accuracy scheme does reduce numerical errors. It is argued that Navier-Stokes calculations on a much finer mesh would improve the solutions, but they would be prohibitively expensive for unsteady calculations.

Original languageEnglish (US)
Pages (from-to)728-738
Number of pages11
JournalJournal of Aircraft
Volume35
Issue number5
DOIs
StatePublished - 1998

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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