EULER CALCULATION FOR FLOW OVER A WING IN GROUND EFFECT.

J. E. Deese; R. K. Agarwal

doi:10.2514/6.1986-1765

EULER CALCULATION FOR FLOW OVER A WING IN GROUND EFFECT.

J. E. Deese, R. K. Agarwal

Research output: Contribution to journal › Conference article › peer-review

6 Scopus citations

Abstract

An Euler solver based on the finite-volume Runge-Kutta time-stepping scheme has been developed to predict the flow around airfoils and wings in ground effect. The technique is applied to a Clark Y-airfoil and a low-aspect-ratio wing (Clark Y-airfoil section) in subsonic flow. Results are compared with experimental data and PANAIR (panel method code) calculations.

Original language	English
Pages (from-to)	10-15
Number of pages	6
Journal	AIAA Paper
DOIs	https://doi.org/10.2514/6.1986-1765
State	Published - 1986

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10.2514/6.1986-1765

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title = "EULER CALCULATION FOR FLOW OVER A WING IN GROUND EFFECT.",

abstract = "An Euler solver based on the finite-volume Runge-Kutta time-stepping scheme has been developed to predict the flow around airfoils and wings in ground effect. The technique is applied to a Clark Y-airfoil and a low-aspect-ratio wing (Clark Y-airfoil section) in subsonic flow. Results are compared with experimental data and PANAIR (panel method code) calculations.",

author = "Deese, {J. E.} and Agarwal, {R. K.}",

year = "1986",

doi = "10.2514/6.1986-1765",

language = "English",

pages = "10--15",

journal = "AIAA Paper",

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T1 - EULER CALCULATION FOR FLOW OVER A WING IN GROUND EFFECT.

AU - Deese, J. E.

AU - Agarwal, R. K.

PY - 1986

Y1 - 1986

N2 - An Euler solver based on the finite-volume Runge-Kutta time-stepping scheme has been developed to predict the flow around airfoils and wings in ground effect. The technique is applied to a Clark Y-airfoil and a low-aspect-ratio wing (Clark Y-airfoil section) in subsonic flow. Results are compared with experimental data and PANAIR (panel method code) calculations.

AB - An Euler solver based on the finite-volume Runge-Kutta time-stepping scheme has been developed to predict the flow around airfoils and wings in ground effect. The technique is applied to a Clark Y-airfoil and a low-aspect-ratio wing (Clark Y-airfoil section) in subsonic flow. Results are compared with experimental data and PANAIR (panel method code) calculations.

UR - http://www.scopus.com/inward/record.url?scp=0022564735&partnerID=8YFLogxK

U2 - 10.2514/6.1986-1765

DO - 10.2514/6.1986-1765

M3 - Conference article

AN - SCOPUS:0022564735

SN - 0146-3705

SP - 10

EP - 15

JO - AIAA Paper

JF - AIAA Paper

ER -

EULER CALCULATION FOR FLOW OVER A WING IN GROUND EFFECT.

Abstract

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