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Wind-tunnel results for an improved 21-percent-thick low-speed airfoil section

Robert McGhee, W. D. Beasley

Open publisher page 2 citations

Abstract

Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000.

About this research paper

What this paper is about

Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000.

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Method / approach

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Available abstract

Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000.

Key concepts: Airfoil, Wind tunnel, Chord (peer-to-peer), Reynolds number, Boundary layer, Relative wind, Adverse pressure gradient, Wind speed

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