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NASA SC(2)-0606 AIRFOIL (sc20606-il)

NASA SC(2)-0606 AIRFOIL - NASA SC(2)-0606 airfoil (NASA TP-2969)


Airfoil sc20606-il
Details Dat file Parser  
(sc20606-il) NASA SC(2)-0606 AIRFOIL
NASA SC(2)-0606 airfoil (NASA TP-2969)
Max thickness 6% at 34% chord.
Max camber 1.3% at 81% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0606 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.004300
 0.005000  0.006500
 0.010000  0.008800
 0.020000  0.011900
 0.030000  0.014000
 0.040000  0.015700
 0.050000  0.017100
 0.060000  0.018300
 0.070000  0.019400
 0.080000  0.020400
 0.090000  0.021300
 0.100000  0.022100
 0.110000  0.022800
 0.120000  0.023500
 0.130000  0.024100
 0.140000  0.024700
 0.150000  0.025200
 0.160000  0.025700
 0.170000  0.026200
 0.180000  0.026600
 0.190000  0.027000
 0.200000  0.027400
 0.210000  0.027700
 0.220000  0.028000
 0.230000  0.028300
 0.240000  0.028600
 0.250000  0.028800
 0.260000  0.029000
 0.270000  0.029200
 0.280000  0.029400
 0.290000  0.029500
 0.300000  0.029600
 0.310000  0.029700
 0.320000  0.029800
 0.330000  0.029900
 0.340000  0.030000
 0.350000  0.030000
 0.360000  0.030000
 0.370000  0.030000
 0.380000  0.030000
 0.390000  0.030000
 0.400000  0.030000
 0.410000  0.030000
 0.420000  0.029900
 0.430000  0.029800
 0.440000  0.029700
 0.450000  0.029600
 0.460000  0.029500
 0.470000  0.029400
 0.480000  0.029200
 0.490000  0.029000
 0.500000  0.028800
 0.510000  0.028600
 0.520000  0.028400
 0.530000  0.028200
 0.540000  0.028000
 0.550000  0.027700
 0.560000  0.027400
 0.570000  0.027100
 0.580000  0.026800
 0.590000  0.026500
 0.600000  0.026200
 0.610000  0.025900
 0.620000  0.025500
 0.630000  0.025100
 0.640000  0.024700
 0.650000  0.024300
 0.660000  0.023900
 0.670000  0.023400
 0.680000  0.022900
 0.690000  0.022400
 0.700000  0.021900
 0.710000  0.021300
 0.720000  0.020700
 0.730000  0.020100
 0.740000  0.019500
 0.750000  0.018900
 0.760000  0.018200
 0.770000  0.017500
 0.780000  0.016800
 0.790000  0.016100
 0.800000  0.015300
 0.810000  0.014500
 0.820000  0.013700
 0.830000  0.012800
 0.840000  0.011900
 0.850000  0.011000
 0.860000  0.010000
 0.870000  0.009000
 0.880000  0.007900
 0.890000  0.006800
 0.900000  0.005600
 0.910000  0.004400
 0.920000  0.003100
 0.930000  0.001800
 0.940000  0.000400
 0.950000 -0.001000
 0.960000 -0.002500
 0.970000 -0.004100
 0.980000 -0.005900
 0.990000 -0.007800
 1.000000 -0.009800

 0.000000  0.000000
 0.002000 -0.004300
 0.005000 -0.006500
 0.010000 -0.008800
 0.020000 -0.011900
 0.030000 -0.014000
 0.040000 -0.015700
 0.050000 -0.017100
 0.060000 -0.018300
 0.070000 -0.019400
 0.080000 -0.020400
 0.090000 -0.021300
 0.100000 -0.022100
 0.110000 -0.022900
 0.120000 -0.023600
 0.130000 -0.024200
 0.140000 -0.024800
 0.150000 -0.025300
 0.160000 -0.025800
 0.170000 -0.026300
 0.180000 -0.026700
 0.190000 -0.027100
 0.200000 -0.027500
 0.210000 -0.027800
 0.220000 -0.028100
 0.230000 -0.028400
 0.240000 -0.028700
 0.250000 -0.028900
 0.260000 -0.029100
 0.270000 -0.029300
 0.280000 -0.029500
 0.290000 -0.029600
 0.300000 -0.029700
 0.310000 -0.029800
 0.320000 -0.029900
 0.330000 -0.030000
 0.340000 -0.030000
 0.350000 -0.030000
 0.360000 -0.030000
 0.370000 -0.030000
 0.380000 -0.029900
 0.390000 -0.029800
 0.400000 -0.029700
 0.410000 -0.029600
 0.420000 -0.029400
 0.430000 -0.029200
 0.440000 -0.029000
 0.450000 -0.028700
 0.460000 -0.028400
 0.470000 -0.028100
 0.480000 -0.027800
 0.490000 -0.027400
 0.500000 -0.027000
 0.510000 -0.026600
 0.520000 -0.026200
 0.530000 -0.025700
 0.540000 -0.025200
 0.550000 -0.024700
 0.560000 -0.024100
 0.570000 -0.023500
 0.580000 -0.022900
 0.590000 -0.022300
 0.600000 -0.021700
 0.610000 -0.021100
 0.620000 -0.020500
 0.630000 -0.019900
 0.640000 -0.019200
 0.650000 -0.018500
 0.660000 -0.017800
 0.670000 -0.017100
 0.680000 -0.016400
 0.690000 -0.015700
 0.700000 -0.015000
 0.710000 -0.014300
 0.720000 -0.013600
 0.730000 -0.012900
 0.740000 -0.012200
 0.750000 -0.011500
 0.760000 -0.010800
 0.770000 -0.010100
 0.780000 -0.009400
 0.790000 -0.008800
 0.800000 -0.008200
 0.810000 -0.007600
 0.820000 -0.007100
 0.830000 -0.006600
 0.840000 -0.006100
 0.850000 -0.005700
 0.860000 -0.005300
 0.870000 -0.005000
 0.880000 -0.004800
 0.890000 -0.004700
 0.900000 -0.004700
 0.910000 -0.004800
 0.920000 -0.005000
 0.930000 -0.005400
 0.940000 -0.005900
 0.950000 -0.006600
 0.960000 -0.007600
 0.970000 -0.008800
 0.980000 -0.010300
 0.990000 -0.012000
 1.000000 -0.013900
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Polars for NASA SC(2)-0606 AIRFOIL (sc20606-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20606-il50,000923.3 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20606-il50,000525.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20606-il100,000931.7 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20606-il100,000535 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20606-il200,000951.8 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20606-il200,000546.2 at α=0.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20606-il500,000972.4 at α=0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20606-il500,000553.6 at α=-0.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20606-il1,000,000982.1 at α=-0.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20606-il1,000,000565.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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