Airfoil sections

Various airfoil sections

xxxx.py are sections defined as a python list of (X, Y) tuples. list[0] = Is (X, Y) of trailing edge and list[0][X] is maximum X list[m] = Where list[m][X] is the minimum value for X, 0

Calculate Reynolds number states R = pVl/u = Vl/v where:

• V = Velocity of the fluid
• l = chord of airfoil
• p = density of the fluid
• u = dynamic viscosity of the fluid
• v = u/p = The kinematic viscosity of the fluid = 1.4207E-5 air 10C or 50F = 1.267E-6 water 10C or 50F

So a small model airplane with a cord of 0.05m or 50mm at 10C

• R = 5 0.05 1.4207E-5 = 17,597 Vmph - 11.185
• = 4 0.05 1.4207E-5 = 14,078 Vmph = 8.948
• = 3 0.05 1.4207E-5 = 10,558 Vmph = 6.711
• = 2 0.05 1.4207E-5 = 7,039 Vmph = 4.474

UIUC Airfoils by Chaaawa

• Eppler thin airfoils
• GOE 63 Airfoil

goe63_points = [[1000,3.5],[949.83,15.03],[899.71,25.76],[799.48,45.61],[699.25,65.47],[599.05,83.43],[498.88,97.9899],[398.8,105.65],[298.79,106.21],[198.86,99.87],[148.95,91.8],[99.0999,79.03],[74.2,69.95],[49.34,57.66],[24.55,39.48],[12.2,26.64],[0,0],[12.66,-14.26],[25.15,-13.51],[50.09,-7.73],[75.02,-1.74],[99.9599,3.74],[149.87,11.31],[199.8,17.38],[299.72,24.42],[399.68,28.26],[499.69,27.3],[599.72,24.14],[699.8,17.88],[799.88,10.72],[899.96,3.56],[949.99,0.83]];

Wikipedia

• NACA airfoil

Information on low Reynolds Number airfoils

• Google Search UIUC low reynolds number airfoils

  • Basic Understanding of Airfoil Characteristics at Low Reynolds Numbers

• Google Search airfoils for reynolds number below 10000

  • 2009 Simplified dragonfly airfoil aerodynamics at Reynolds numbers below 8000 A quote: "The aerodynamic performance (such as mean and fluctuating lift and drag), are first compared to a “traditional” low Reynolds number airfoil: the Eppler-E61. The numerical results demonstrate superior performances of the corrugated airfoil."

  • 2019 Aerodynamic shape optimization of airfoils at ultra-low Reynolds numbers A quote: "The optimal airfoils have evolved into rather thin profiles with distinct droops near the leading and trailing edges. The leading edge droop varies from about 7.3% for Re = 1000 to about 1.9% for Re = 10000. This droop occurs at about x/c = 0.28. The droop near the trailing edge varies from about 3.4% for Re = 1000 to about 2.4% for Re = 10000, occurring at x/c = 0.8. The maximum thickness of the optimal airfoils was about 6% and its chordwise location varied from x/c = 0.1 for Re = 1000 and moving aft till x/c = 0.23 for Re = 10000. A smooth cavity in between the droops is clearly perceptible on the upper surface of the airfoil near the mid-chord. We shall explain how the flow structure in this cavity enhances the lift of the airfoil. The upper surface cavity slowly diminishes with increasing Re. It is also noted that maximum t/c gradually increases with Re"

  • 2011 Experimentall Flow Visualization for Corrugated Airfoils at Low Reynolds Number Includeing Development of a Pithc and Plunge Fixture

• "Analysis, design and testing of airfoils for use at ultra-low Reynolds numbers" [pdf]