New blockage-correction method for separated flows in a subsonic wind tunnel

Seung Hee Kang; Seung Ki Ahn; Oh Joon Kwon

doi:10.2514/1.15401

New blockage-correction method for separated flows in a subsonic wind tunnel

Seung Hee Kang^*
, Seung Ki Ahn
, Oh Joon Kwon

^*Corresponding author for this work

Department of Aerospace Engineering

Korea Advanced Institute of Science and Technology
Korean Agency for Defense Development
Wind Tunnel Test Division
AIAA

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

1 Scopus citations

Abstract

A separation blockage correction method for aircraft is developed for subsonic wind tunnels with a closed test section. The proposed method can be applied continuously from the low-angle region to the highly nonlinear posstall region, It is shown that the results by the present correction method based on the nonlinear relationship between the separation blockage and separation drag are in good agreement with those of the measured-boundary-condition method. The proposed separation-blockage-correction method provides accurate wall correction for separated flows around realistic aircraft configurations for closed test-section subsonic wind tunnels.

Original language	English
Pages (from-to)	1352-1354
Number of pages	3
Journal	Journal of Aircraft
Volume	42
Issue number	5
DOIs	https://doi.org/10.2514/1.15401
State	Published - 2005

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10.2514/1.15401

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title = "New blockage-correction method for separated flows in a subsonic wind tunnel",

abstract = "A separation blockage correction method for aircraft is developed for subsonic wind tunnels with a closed test section. The proposed method can be applied continuously from the low-angle region to the highly nonlinear posstall region, It is shown that the results by the present correction method based on the nonlinear relationship between the separation blockage and separation drag are in good agreement with those of the measured-boundary-condition method. The proposed separation-blockage-correction method provides accurate wall correction for separated flows around realistic aircraft configurations for closed test-section subsonic wind tunnels.",

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AU - Kwon, Oh Joon

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N2 - A separation blockage correction method for aircraft is developed for subsonic wind tunnels with a closed test section. The proposed method can be applied continuously from the low-angle region to the highly nonlinear posstall region, It is shown that the results by the present correction method based on the nonlinear relationship between the separation blockage and separation drag are in good agreement with those of the measured-boundary-condition method. The proposed separation-blockage-correction method provides accurate wall correction for separated flows around realistic aircraft configurations for closed test-section subsonic wind tunnels.

AB - A separation blockage correction method for aircraft is developed for subsonic wind tunnels with a closed test section. The proposed method can be applied continuously from the low-angle region to the highly nonlinear posstall region, It is shown that the results by the present correction method based on the nonlinear relationship between the separation blockage and separation drag are in good agreement with those of the measured-boundary-condition method. The proposed separation-blockage-correction method provides accurate wall correction for separated flows around realistic aircraft configurations for closed test-section subsonic wind tunnels.

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DO - 10.2514/1.15401

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ER -

New blockage-correction method for separated flows in a subsonic wind tunnel

Abstract

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