EULER AERODYNAMIC METHOD FOR LEADING-EDGE VORTEX FLOW SIMULATION.

Pradeep Raj, Lyle Norman Long

Research output: Contribution to journalArticle

3 Citations (Scopus)

Abstract

This paper describes the current capabilities and the future plans for a three-dimensional Euler Aerodynamic Method. The basic solution algorithm is based on the finite-volume, Runge-Kutta pseudo-time-stepping scheme of FLO-57. Several modifications to improve accuracy and computational efficiency have been incorporated and others are being investigated. The computer code is used to analyze a cropped delta wing at 0. 6 Mach number and and arrow wing at 0. 85 Mach number. Computed aerodynamic parameters are compared with experimental data. In all cases, the configuration is impulsively started and no Kutta condition is applied at sharp edges.

Original languageEnglish (US)
Pages (from-to)263-281
Number of pages19
JournalNASA Conference Publication
StatePublished - 1986

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Flow simulation
Mach number
Aerodynamics
Vortex flow
Computational efficiency

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Raj, Pradeep ; Long, Lyle Norman. / EULER AERODYNAMIC METHOD FOR LEADING-EDGE VORTEX FLOW SIMULATION. In: NASA Conference Publication. 1986 ; pp. 263-281.
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EULER AERODYNAMIC METHOD FOR LEADING-EDGE VORTEX FLOW SIMULATION. / Raj, Pradeep; Long, Lyle Norman.

In: NASA Conference Publication, 1986, p. 263-281.

Research output: Contribution to journalArticle

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