Turbulent-flow calculations for flow over wings near maximum lift

J. E. Deese; R. K. Agarwal

doi:10.2514/3.45962

Turbulent-flow calculations for flow over wings near maximum lift

J. E. Deese, R. K. Agarwal

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2 Scopus citations

Abstract

The calculation of horizontal stabilizer flowfields near maximum lift using a three-dimensional Navier-Stokes code is described. Results are presented for two stabilizer configurations with and without elevator deflection. Predicted lift coefficients are within 10% of experimental values up to the onset of stall. The code is able to predict the onset of both wing and elevator stall for the two configurations studied. Surface pressure distribution predictions are hi good agreement with experimental data.

Original language	English
Pages (from-to)	929-935
Number of pages	7
Journal	Journal of Aircraft
Volume	27
Issue number	11
DOIs	https://doi.org/10.2514/3.45962
State	Published - Nov 1990

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title = "Turbulent-flow calculations for flow over wings near maximum lift",

abstract = "The calculation of horizontal stabilizer flowfields near maximum lift using a three-dimensional Navier-Stokes code is described. Results are presented for two stabilizer configurations with and without elevator deflection. Predicted lift coefficients are within 10% of experimental values up to the onset of stall. The code is able to predict the onset of both wing and elevator stall for the two configurations studied. Surface pressure distribution predictions are hi good agreement with experimental data.",

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

year = "1990",

month = nov,

doi = "10.2514/3.45962",

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N2 - The calculation of horizontal stabilizer flowfields near maximum lift using a three-dimensional Navier-Stokes code is described. Results are presented for two stabilizer configurations with and without elevator deflection. Predicted lift coefficients are within 10% of experimental values up to the onset of stall. The code is able to predict the onset of both wing and elevator stall for the two configurations studied. Surface pressure distribution predictions are hi good agreement with experimental data.

AB - The calculation of horizontal stabilizer flowfields near maximum lift using a three-dimensional Navier-Stokes code is described. Results are presented for two stabilizer configurations with and without elevator deflection. Predicted lift coefficients are within 10% of experimental values up to the onset of stall. The code is able to predict the onset of both wing and elevator stall for the two configurations studied. Surface pressure distribution predictions are hi good agreement with experimental data.

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DO - 10.2514/3.45962

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VL - 27

SP - 929

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JO - Journal of Aircraft

JF - Journal of Aircraft

IS - 11

ER -

Turbulent-flow calculations for flow over wings near maximum lift

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