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NASA SC(2)-1006 AIRFOIL (sc21006-il)

NASA SC(2)-1006 AIRFOIL - NASA SC(2)-1006 airfoil


Airfoil sc21006-il
Details Dat file Parser  
(sc21006-il) NASA SC(2)-1006 AIRFOIL
NASA SC(2)-1006 airfoil
Max thickness 6% at 30% chord.
Max camber 2.6% at 73% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-1006 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.004200
 0.005000  0.006400
 0.010000  0.008700
 0.020000  0.011700
 0.030000  0.014000
 0.040000  0.015800
 0.050000  0.017400
 0.060000  0.018800
 0.070000  0.020000
 0.080000  0.021100
 0.090000  0.022100
 0.100000  0.023000
 0.110000  0.023800
 0.120000  0.024500
 0.130000  0.025200
 0.140000  0.025800
 0.150000  0.026400
 0.160000  0.026900
 0.170000  0.027400
 0.180000  0.027800
 0.190000  0.028200
 0.200000  0.028500
 0.210000  0.028800
 0.220000  0.029100
 0.230000  0.029300
 0.240000  0.029500
 0.250000  0.029700
 0.260000  0.029800
 0.270000  0.029900
 0.280000  0.030000
 0.290000  0.030000
 0.300000  0.030000
 0.310000  0.030000
 0.320000  0.030000
 0.330000  0.029900
 0.340000  0.029800
 0.350000  0.029700
 0.360000  0.029600
 0.370000  0.029400
 0.380000  0.029200
 0.390000  0.029000
 0.400000  0.028800
 0.410000  0.028600
 0.420000  0.028300
 0.430000  0.028000
 0.440000  0.027700
 0.450000  0.027400
 0.460000  0.027000
 0.470000  0.026600
 0.480000  0.026200
 0.490000  0.025800
 0.500000  0.025400
 0.510000  0.024900
 0.520000  0.024400
 0.530000  0.023900
 0.540000  0.023400
 0.550000  0.022900
 0.560000  0.022300
 0.570000  0.021700
 0.580000  0.021100
 0.590000  0.020500
 0.600000  0.019800
 0.610000  0.019100
 0.620000  0.018400
 0.630000  0.017700
 0.640000  0.016900
 0.650000  0.016100
 0.660000  0.015300
 0.670000  0.014400
 0.680000  0.013500
 0.690000  0.012600
 0.700000  0.011700
 0.710000  0.010700
 0.720000  0.009700
 0.730000  0.008700
 0.740000  0.007600
 0.750000  0.006500
 0.760000  0.005300
 0.770000  0.004100
 0.780000  0.002800
 0.790000  0.001500
 0.800000  0.000100
 0.810000 -0.001400
 0.820000 -0.003000
 0.830000 -0.004600
 0.840000 -0.006300
 0.850000 -0.008100
 0.860000 -0.010000
 0.870000 -0.012000
 0.880000 -0.014100
 0.890000 -0.016200
 0.900000 -0.018400
 0.910000 -0.020600
 0.920000 -0.022900
 0.930000 -0.025300
 0.940000 -0.027700
 0.950000 -0.030200
 0.960000 -0.032800
 0.970000 -0.035500
 0.980000 -0.038300
 0.990000 -0.041200
 1.000000 -0.044300

 0.000000  0.000000
 0.002000 -0.004200
 0.005000 -0.006400
 0.010000 -0.008700
 0.020000 -0.011700
 0.030000 -0.014000
 0.040000 -0.015800
 0.050000 -0.017400
 0.060000 -0.018700
 0.070000 -0.019900
 0.080000 -0.020900
 0.090000 -0.021800
 0.100000 -0.022600
 0.110000 -0.023400
 0.120000 -0.024100
 0.130000 -0.024700
 0.140000 -0.025300
 0.150000 -0.025900
 0.160000 -0.026400
 0.170000 -0.026900
 0.180000 -0.027300
 0.190000 -0.027700
 0.200000 -0.028100
 0.210000 -0.028400
 0.220000 -0.028700
 0.230000 -0.029000
 0.240000 -0.029200
 0.250000 -0.029400
 0.260000 -0.029600
 0.270000 -0.029700
 0.280000 -0.029800
 0.290000 -0.029900
 0.300000 -0.030000
 0.310000 -0.030000
 0.320000 -0.030000
 0.330000 -0.030000
 0.340000 -0.030000
 0.350000 -0.030000
 0.360000 -0.029900
 0.370000 -0.029800
 0.380000 -0.029700
 0.390000 -0.029600
 0.400000 -0.029500
 0.410000 -0.029400
 0.420000 -0.029300
 0.430000 -0.029200
 0.440000 -0.029100
 0.450000 -0.029000
 0.460000 -0.028900
 0.470000 -0.028700
 0.480000 -0.028500
 0.490000 -0.028200
 0.500000 -0.028100
 0.510000 -0.027900
 0.520000 -0.027700
 0.530000 -0.027500
 0.540000 -0.027300
 0.550000 -0.027100
 0.560000 -0.026900
 0.570000 -0.026700
 0.580000 -0.026500
 0.590000 -0.026300
 0.600000 -0.026100
 0.610000 -0.025900
 0.620000 -0.025700
 0.630000 -0.025500
 0.640000 -0.025300
 0.650000 -0.025100
 0.660000 -0.024900
 0.670000 -0.024700
 0.680000 -0.024500
 0.690000 -0.024300
 0.700000 -0.024100
 0.710000 -0.023900
 0.720000 -0.023700
 0.730000 -0.023600
 0.740000 -0.023500
 0.750000 -0.023400
 0.760000 -0.023300
 0.770000 -0.023300
 0.780000 -0.023300
 0.790000 -0.023300
 0.800000 -0.023400
 0.810000 -0.023500
 0.820000 -0.023700
 0.830000 -0.023900
 0.840000 -0.024200
 0.850000 -0.024600
 0.860000 -0.025100
 0.870000 -0.025700
 0.880000 -0.026400
 0.890000 -0.027200
 0.900000 -0.028100
 0.910000 -0.029200
 0.920000 -0.030500
 0.930000 -0.032000
 0.940000 -0.033700
 0.950000 -0.035600
 0.960000 -0.037700
 0.970000 -0.040000
 0.980000 -0.042500
 0.990000 -0.045200
 1.000000 -0.048200
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Lednicer format dat file
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Polars for NASA SC(2)-1006 AIRFOIL (sc21006-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc21006-il50,000928.3 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21006-il50,000529.8 at α=0.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21006-il100,000939.2 at α=0.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21006-il100,000548.9 at α=-0.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21006-il200,000966.5 at α=-0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21006-il200,000561.3 at α=-1°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21006-il500,0009101.9 at α=-1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21006-il500,000592 at α=-2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21006-il1,000,0009130.4 at α=-2°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21006-il1,000,0005100.2 at α=-3°Mach=0 Ncrit=5Xfoil predictionDetails
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