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NASA SC(2)-0406 AIRFOIL (sc20406-il)

NASA SC(2)-0406 AIRFOIL - NASA SC(2)-0406 airfoil (NASA TP-2969)


Airfoil sc20406-il
Details Dat file Parser  
(sc20406-il) NASA SC(2)-0406 AIRFOIL
NASA SC(2)-0406 airfoil (NASA TP-2969)
Max thickness 6% at 35% chord.
Max camber 0.6% at 79% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0406 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.004300
 0.005000  0.006400
 0.010000  0.008900
 0.020000  0.012200
 0.030000  0.014400
 0.040000  0.016100
 0.050000  0.017500
 0.060000  0.018700
 0.070000  0.019800
 0.080000  0.020700
 0.090000  0.021500
 0.100000  0.022300
 0.110000  0.023000
 0.120000  0.023600
 0.130000  0.024200
 0.140000  0.024800
 0.150000  0.025300
 0.160000  0.025800
 0.170000  0.026200
 0.180000  0.026600
 0.190000  0.027000
 0.200000  0.027300
 0.210000  0.027600
 0.220000  0.027900
 0.230000  0.028200
 0.240000  0.028500
 0.250000  0.028700
 0.260000  0.028900
 0.270000  0.029100
 0.280000  0.029300
 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  0.030100
 0.360000  0.030100
 0.370000  0.030100
 0.380000  0.030100
 0.390000  0.030100
 0.400000  0.030100
 0.410000  0.030100
 0.420000  0.030000
 0.430000  0.029900
 0.440000  0.029800
 0.450000  0.029700
 0.460000  0.029600
 0.470000  0.029500
 0.480000  0.029400
 0.490000  0.029200
 0.500000  0.029000
 0.510000  0.028800
 0.520000  0.028600
 0.530000  0.028400
 0.540000  0.028200
 0.550000  0.027900
 0.560000  0.027600
 0.570000  0.027300
 0.580000  0.027000
 0.590000  0.026700
 0.600000  0.026300
 0.610000  0.025900
 0.620000  0.025500
 0.630000  0.025100
 0.640000  0.024700
 0.650000  0.024200
 0.660000  0.023700
 0.670000  0.023200
 0.680000  0.022700
 0.690000  0.022200
 0.700000  0.021700
 0.710000  0.021100
 0.720000  0.020500
 0.730000  0.019900
 0.740000  0.019300
 0.750000  0.018700
 0.760000  0.018100
 0.770000  0.017400
 0.780000  0.016700
 0.790000  0.016000
 0.800000  0.015300
 0.810000  0.014600
 0.820000  0.013900
 0.830000  0.013200
 0.840000  0.012400
 0.850000  0.011600
 0.860000  0.010800
 0.870000  0.010000
 0.880000  0.009200
 0.890000  0.008400
 0.900000  0.007600
 0.910000  0.006800
 0.920000  0.005900
 0.930000  0.005000
 0.940000  0.004100
 0.950000  0.003200
 0.960000  0.002300
 0.970000  0.001400
 0.980000  0.000400
 0.990000 -0.000600
 1.000000 -0.001600

 0.000000  0.000000
 0.002000 -0.004300
 0.005000 -0.006400
 0.010000 -0.008900
 0.020000 -0.012200
 0.030000 -0.014400
 0.040000 -0.016100
 0.050000 -0.017500
 0.060000 -0.018700
 0.070000 -0.019700
 0.080000 -0.020600
 0.090000 -0.021500
 0.100000 -0.022300
 0.110000 -0.023000
 0.120000 -0.023700
 0.130000 -0.024300
 0.140000 -0.024900
 0.150000 -0.025400
 0.160000 -0.025900
 0.170000 -0.026400
 0.180000 -0.026800
 0.190000 -0.027200
 0.200000 -0.027600
 0.210000 -0.027900
 0.220000 -0.028200
 0.230000 -0.028500
 0.240000 -0.028800
 0.250000 -0.029000
 0.260000 -0.029200
 0.270000 -0.029400
 0.280000 -0.029600
 0.290000 -0.029700
 0.300000 -0.029800
 0.310000 -0.029900
 0.320000 -0.030000
 0.330000 -0.030100
 0.340000 -0.030100
 0.350000 -0.030100
 0.360000 -0.030100
 0.370000 -0.030100
 0.380000 -0.030000
 0.390000 -0.029900
 0.400000 -0.029800
 0.410000 -0.029700
 0.420000 -0.029500
 0.430000 -0.029300
 0.440000 -0.029100
 0.450000 -0.028800
 0.460000 -0.028500
 0.470000 -0.028200
 0.480000 -0.027900
 0.490000 -0.027500
 0.500000 -0.027100
 0.510000 -0.026700
 0.520000 -0.026300
 0.530000 -0.025800
 0.540000 -0.025300
 0.550000 -0.024800
 0.560000 -0.024300
 0.570000 -0.023700
 0.580000 -0.023100
 0.590000 -0.022500
 0.600000 -0.021900
 0.610000 -0.021300
 0.620000 -0.020700
 0.630000 -0.020100
 0.640000 -0.019500
 0.650000 -0.018800
 0.660000 -0.018100
 0.670000 -0.017400
 0.680000 -0.016700
 0.690000 -0.016000
 0.700000 -0.015300
 0.710000 -0.014600
 0.720000 -0.013900
 0.730000 -0.013200
 0.740000 -0.012500
 0.750000 -0.011800
 0.760000 -0.011100
 0.770000 -0.010400
 0.780000 -0.009700
 0.790000 -0.009000
 0.800000 -0.008400
 0.810000 -0.007800
 0.820000 -0.007200
 0.830000 -0.006600
 0.840000 -0.006000
 0.850000 -0.005500
 0.860000 -0.005000
 0.870000 -0.004500
 0.880000 -0.004100
 0.890000 -0.003700
 0.900000 -0.003400
 0.910000 -0.003100
 0.920000 -0.002900
 0.930000 -0.002800
 0.940000 -0.002800
 0.950000 -0.002900
 0.960000 -0.003100
 0.970000 -0.003400
 0.980000 -0.003900
 0.990000 -0.004600
 1.000000 -0.005500
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Lednicer format dat file
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Polars for NASA SC(2)-0406 AIRFOIL (sc20406-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20406-il50,000920.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20406-il50,000524.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20406-il100,000937.2 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20406-il100,000532.3 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20406-il200,000947.5 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20406-il200,000536.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20406-il500,000952.9 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20406-il500,000550.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20406-il1,000,000959.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20406-il1,000,000561.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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