Experiments in Fluids

, Volume 23, Issue 5, pp 405–409

Wind tunnel tests of wings at Reynolds numbers below 70 000

  • E. V. Laitone

Abstract

 Rectangular planform wings were tested at Reynolds numbers as low as 20 000 in a low turbulence wind tunnel. The lift and drag measurements on a NACA 0012 profile were compared with those for thin flat and cambered plates. For all Reynolds numbers below 70 000 the best profile was a thin plate with a 5% circular arc camber. At all turbulence levels this profile produced the greatest lift-drag ratio, and had the highest lift coefficient at all angles of attack. The 5% camber and all of the thin plates tested were relatively insensitive to either a variation in the Reynolds number, or an increase in the wind tunnel turbulence level, whereas the NACA 0012 was very seriously affected by either, at Reynolds numbers below 50 000.

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Copyright information

© Springer-Verlag Berlin Heidelberg 1997

Authors and Affiliations

  • E. V. Laitone
    • 1
  1. 1.Department of Mechanical Engineering University of California Berkeley, CA 94702, USAUS

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