Surface oil flow measurements on several airfoils at low Reynolds numbers

Bryan D. McGranahan; Michael S Selig

doi:10.2514/6.2003-4067

Surface oil flow measurements on several airfoils at low Reynolds numbers

Bryan D. McGranahan, Michael S Selig

Aerospace Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

Measurements made of upper-surface flow features on the following airfoils is presented: E387, FX 63-137, NASA NLF(1)-0414F, S822, S8036, SD7003, and SD7037 at Reynolds numbers of 200,000, 350,000, and 500,000. Oil-flow visualization of the upper-surface flow features is discussed in detail and comparisons are made between present work and data acquired at the NASA Langley Low-Turbulence Pressure Tunnel (LTPT). Drag polars for the airfoils tested at Reynolds numbers of 200,000, 350,000, and 500,000 are presented allowing a direct comparison between surface flow features and airfoil performance. Also presented is a comparison of upper-surface flow features computed by XFOIL with those measured in the UIUC wind tunnel for Reynolds numbers of 200,000, 350,000, and 500,000.

Original language	English (US)
Title of host publication	21st AIAA Applied Aerodynamics Conference
DOIs	https://doi.org/10.2514/6.2003-4067
State	Published - Dec 1 2003
Event	21st AIAA Applied Aerodynamics Conference 2003 - Orlando, FL, United States Duration: Jun 23 2003 → Jun 26 2003

Publication series

Name	21st AIAA Applied Aerodynamics Conference

Other

Other	21st AIAA Applied Aerodynamics Conference 2003
Country/Territory	United States
City	Orlando, FL
Period	6/23/03 → 6/26/03

ASJC Scopus subject areas

Aerospace Engineering
Mechanical Engineering

Online availability

10.2514/6.2003-4067

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Cite this

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title = "Surface oil flow measurements on several airfoils at low Reynolds numbers",

abstract = "Measurements made of upper-surface flow features on the following airfoils is presented: E387, FX 63-137, NASA NLF(1)-0414F, S822, S8036, SD7003, and SD7037 at Reynolds numbers of 200,000, 350,000, and 500,000. Oil-flow visualization of the upper-surface flow features is discussed in detail and comparisons are made between present work and data acquired at the NASA Langley Low-Turbulence Pressure Tunnel (LTPT). Drag polars for the airfoils tested at Reynolds numbers of 200,000, 350,000, and 500,000 are presented allowing a direct comparison between surface flow features and airfoil performance. Also presented is a comparison of upper-surface flow features computed by XFOIL with those measured in the UIUC wind tunnel for Reynolds numbers of 200,000, 350,000, and 500,000.",

author = "McGranahan, {Bryan D.} and Selig, {Michael S}",

year = "2003",

month = dec,

day = "1",

doi = "10.2514/6.2003-4067",

language = "English (US)",

isbn = "9781624100925",

series = "21st AIAA Applied Aerodynamics Conference",

booktitle = "21st AIAA Applied Aerodynamics Conference",

note = "21st AIAA Applied Aerodynamics Conference 2003 ; Conference date: 23-06-2003 Through 26-06-2003",

}

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T1 - Surface oil flow measurements on several airfoils at low Reynolds numbers

AU - McGranahan, Bryan D.

AU - Selig, Michael S

PY - 2003/12/1

Y1 - 2003/12/1

N2 - Measurements made of upper-surface flow features on the following airfoils is presented: E387, FX 63-137, NASA NLF(1)-0414F, S822, S8036, SD7003, and SD7037 at Reynolds numbers of 200,000, 350,000, and 500,000. Oil-flow visualization of the upper-surface flow features is discussed in detail and comparisons are made between present work and data acquired at the NASA Langley Low-Turbulence Pressure Tunnel (LTPT). Drag polars for the airfoils tested at Reynolds numbers of 200,000, 350,000, and 500,000 are presented allowing a direct comparison between surface flow features and airfoil performance. Also presented is a comparison of upper-surface flow features computed by XFOIL with those measured in the UIUC wind tunnel for Reynolds numbers of 200,000, 350,000, and 500,000.

AB - Measurements made of upper-surface flow features on the following airfoils is presented: E387, FX 63-137, NASA NLF(1)-0414F, S822, S8036, SD7003, and SD7037 at Reynolds numbers of 200,000, 350,000, and 500,000. Oil-flow visualization of the upper-surface flow features is discussed in detail and comparisons are made between present work and data acquired at the NASA Langley Low-Turbulence Pressure Tunnel (LTPT). Drag polars for the airfoils tested at Reynolds numbers of 200,000, 350,000, and 500,000 are presented allowing a direct comparison between surface flow features and airfoil performance. Also presented is a comparison of upper-surface flow features computed by XFOIL with those measured in the UIUC wind tunnel for Reynolds numbers of 200,000, 350,000, and 500,000.

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M3 - Conference contribution

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BT - 21st AIAA Applied Aerodynamics Conference

T2 - 21st AIAA Applied Aerodynamics Conference 2003

Y2 - 23 June 2003 through 26 June 2003

ER -

Surface oil flow measurements on several airfoils at low Reynolds numbers

Abstract

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