Wing-tip vortex calculations using a high-accuracy scheme

David P. Lockard, Philip J. Morris

Research output: Contribution to journalArticlepeer-review

11 Scopus citations


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
Issue number5
StatePublished - 1998

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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