Correlation of Theory to Wind-Tunnel Data at Reynolds Numbers below 500,000

  • Raquel Evangelista
  • Robert J. McGhee
  • Betty S. Walker
Part of the Lecture Notes in Engineering book series (LNENG, volume 54)

Abstract

This paper presents results obtained from two airfoil analysis methods compared with previously published wind tunnel test data at chord Reynolds numbers below 500,000. The analysis methods are from the Eppler-Somers airfoil design/analysis code and from ISES, the Drela-Giles airfoil design/analysis code. The experimental data are from recent tests of the Eppler 387 airfoil in the NASA Langley Low Turbulence Pressure Tunnel. For R ≥ 200,000, lift and pitching moment predictions from both theories compare well with experiment. Drag predictions from both theories also agree with experiment, although to different degrees. The Drela-Giles code also predicts pressure distributions which compare well with the experimental pressure distributions, including those cases with laminar separation bubbles. For Reynolds numbers of 60,000 and 100,000, lift and pitching moment predictions from both theories are in fair agreement with experiment. However, most of the drag predictions from the Eppler-Somers code are accompanied with separation bubble warnings which indicate that the drag predictions are too low. With the Drela-Giles code, there is a large discrepancy between the computed and experimental pressure distributions in cases with laminar separation bubbles, although the drag polar predictions are similar in trend to experiment.

Keywords

Eter 

Symbol List

c

airfoil chord

cd

airfoil section drag coefficient

cl

airfoil section lift coefficient

cl,max

maximum airfoil section lift coefficient

cm

airfoil section quarter-chord pitching moment coefficient

Cp

pressure coefficient

n

critical disturbance amplification ratio (transition criterion in Drela-Giles code)

R

Reynolds number based on airfoil chord and freestream conditions

x

airfoil abscissa

(x/c)Tr

theoretical transition location and experimental turbulent reattachment location

α

angle of attack relative to chord line, degrees

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References

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Copyright information

© Springer-Verlag Berlin, Heidelberg 1989

Authors and Affiliations

  • Raquel Evangelista
    • 1
  • Robert J. McGhee
    • 2
  • Betty S. Walker
    • 2
  1. 1.Analytical Services & Materials, Inc.HamptonUSA
  2. 2.NASA Langley Research CenterHamptonUSA

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