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S5010 (s5010-il)

S5010 - Selig S5010 low Reynolds number airfoil


Airfoil s5010-il
Details Dat file Parser  
(s5010-il) S5010
Selig S5010 low Reynolds number airfoil
Max thickness 9.8% at 27.6% chord.
Max camber 1.8% at 32% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S5010
         1.0000000      0.0000000
         0.9967600      0.0000100
         0.9870700      0.0000700
         0.9710100      0.0003600
         0.9487000      0.0010800
         0.9204100      0.0025600
         0.8866700      0.0051600
         0.8482800      0.0090300
         0.8060800      0.0140600
         0.7607600      0.0200800
         0.7130700      0.0268800
         0.6637700      0.0342000
         0.6135500      0.0416300
         0.5629600      0.0487700
         0.5124700      0.0552900
         0.4625100      0.0609300
         0.4134600      0.0654600
         0.3657600      0.0687300
         0.3196900      0.0706300
         0.2756000      0.0711300
         0.2338300      0.0702300
         0.1947300      0.0679900
         0.1586000      0.0644500
         0.1257300      0.0596800
         0.0963700      0.0537700
         0.0707100      0.0468800
         0.0488900      0.0391500
         0.0310200      0.0308100
         0.0171800      0.0221400
         0.0073900      0.0134800
         0.0016700      0.0053300
         0.0001500     -0.0014000
         0.0042400     -0.0065000
         0.0145600     -0.0108400
         0.0302800     -0.0147100
         0.0512300     -0.0180400
         0.0771800     -0.0208200
         0.1078500     -0.0230600
         0.1429100     -0.0248100
         0.1819400     -0.0260900
         0.2244800     -0.0268800
         0.2700800     -0.0271500
         0.3182900     -0.0269100
         0.3686400     -0.0262300
         0.4205500     -0.0251700
         0.4734500     -0.0238100
         0.5267500     -0.0221900
         0.5798300     -0.0203900
         0.6320900     -0.0184600
         0.6829200     -0.0164500
         0.7317300     -0.0144300
         0.7779200     -0.0124300
         0.8209500     -0.0104900
         0.8603000     -0.0086500
         0.8954700     -0.0069100
         0.9260300     -0.0052700
         0.9516300     -0.0036700
         0.9721100     -0.0021200
         0.9873000     -0.0008800
         0.9967800     -0.0001900
         1.0000000      0.0000000
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Polars for S5010 (s5010-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s5010-il50,000924.1 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s5010-il50,000532.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   s5010-il100,000945 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s5010-il100,000547.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   s5010-il200,000963.2 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s5010-il200,000562.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s5010-il500,000986.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s5010-il500,000580.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s5010-il1,000,0009102.8 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s5010-il1,000,000594.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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