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NASA SC(2)-0410 AIRFOIL (sc20410-il)

NASA SC(2)-0410 AIRFOIL - NASA SC(2)-0410 airfoil (NASA TP-2969)


Airfoil sc20410-il
Details Dat file Parser  
(sc20410-il) NASA SC(2)-0410 AIRFOIL
NASA SC(2)-0410 airfoil (NASA TP-2969)
Max thickness 10% at 38% chord.
Max camber 1.1% at 85% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0410 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.007600
 0.005000  0.011600
 0.010000  0.015500
 0.020000  0.020700
 0.030000  0.024200
 0.040000  0.026900
 0.050000  0.029100
 0.060000  0.031000
 0.070000  0.032700
 0.080000  0.034200
 0.090000  0.035600
 0.100000  0.036800
 0.110000  0.037900
 0.120000  0.038900
 0.130000  0.039900
 0.140000  0.040800
 0.150000  0.041600
 0.160000  0.042400
 0.170000  0.043100
 0.180000  0.043800
 0.190000  0.044400
 0.200000  0.045000
 0.210000  0.045600
 0.220000  0.046100
 0.230000  0.046600
 0.240000  0.047000
 0.250000  0.047400
 0.260000  0.047800
 0.270000  0.048100
 0.280000  0.048400
 0.290000  0.048700
 0.300000  0.048900
 0.310000  0.049100
 0.320000  0.049300
 0.330000  0.049500
 0.340000  0.049600
 0.350000  0.049700
 0.360000  0.049800
 0.370000  0.049900
 0.380000  0.050000
 0.390000  0.050000
 0.400000  0.050000
 0.410000  0.050000
 0.420000  0.050000
 0.430000  0.050000
 0.440000  0.049900
 0.450000  0.049800
 0.460000  0.049700
 0.470000  0.049600
 0.480000  0.049400
 0.490000  0.049200
 0.500000  0.049000
 0.510000  0.048800
 0.520000  0.048500
 0.530000  0.048200
 0.540000  0.047900
 0.550000  0.047600
 0.560000  0.047200
 0.570000  0.046800
 0.580000  0.046400
 0.590000  0.045900
 0.600000  0.045400
 0.610000  0.044900
 0.620000  0.044300
 0.630000  0.043700
 0.640000  0.043100
 0.650000  0.042500
 0.660000  0.041800
 0.670000  0.041100
 0.680000  0.040400
 0.690000  0.039600
 0.700000  0.038800
 0.710000  0.038000
 0.720000  0.037200
 0.730000  0.036300
 0.740000  0.035400
 0.750000  0.034500
 0.760000  0.033600
 0.770000  0.032600
 0.780000  0.031600
 0.790000  0.030600
 0.800000  0.029600
 0.810000  0.028500
 0.820000  0.027400
 0.830000  0.026300
 0.840000  0.025200
 0.850000  0.024100
 0.860000  0.022900
 0.870000  0.021700
 0.880000  0.020500
 0.890000  0.019300
 0.900000  0.018000
 0.910000  0.016700
 0.920000  0.015400
 0.930000  0.014100
 0.940000  0.012700
 0.950000  0.011300
 0.960000  0.009800
 0.970000  0.008300
 0.980000  0.006700
 0.990000  0.005000
 1.000000  0.003200

 0.000000  0.000000
 0.002000 -0.007600
 0.005000 -0.011600
 0.010000 -0.015500
 0.020000 -0.020700
 0.030000 -0.024200
 0.040000 -0.026900
 0.050000 -0.029100
 0.060000 -0.031000
 0.070000 -0.032700
 0.080000 -0.034200
 0.090000 -0.035600
 0.100000 -0.036900
 0.110000 -0.038100
 0.120000 -0.039200
 0.130000 -0.040200
 0.140000 -0.041100
 0.150000 -0.042000
 0.160000 -0.042800
 0.170000 -0.043500
 0.180000 -0.044200
 0.190000 -0.044900
 0.200000 -0.045500
 0.210000 -0.046000
 0.220000 -0.046500
 0.230000 -0.047000
 0.240000 -0.047400
 0.250000 -0.047800
 0.260000 -0.048100
 0.270000 -0.048400
 0.280000 -0.048700
 0.290000 -0.048900
 0.300000 -0.049100
 0.310000 -0.049300
 0.320000 -0.049400
 0.330000 -0.049500
 0.340000 -0.049600
 0.350000 -0.049700
 0.360000 -0.049700
 0.370000 -0.049700
 0.380000 -0.049700
 0.390000 -0.049600
 0.400000 -0.049500
 0.410000 -0.049400
 0.420000 -0.049200
 0.430000 -0.049000
 0.440000 -0.048800
 0.450000 -0.048500
 0.460000 -0.048200
 0.470000 -0.047800
 0.480000 -0.047400
 0.490000 -0.047000
 0.500000 -0.046500
 0.510000 -0.046000
 0.520000 -0.045400
 0.530000 -0.044700
 0.540000 -0.044000
 0.550000 -0.043200
 0.560000 -0.042300
 0.570000 -0.041300
 0.580000 -0.040200
 0.590000 -0.039000
 0.600000 -0.037800
 0.610000 -0.036500
 0.620000 -0.035200
 0.630000 -0.033800
 0.640000 -0.032400
 0.650000 -0.030900
 0.660000 -0.029400
 0.670000 -0.027800
 0.680000 -0.026200
 0.690000 -0.024600
 0.700000 -0.023000
 0.710000 -0.021400
 0.720000 -0.019800
 0.730000 -0.018200
 0.740000 -0.016600
 0.750000 -0.015000
 0.760000 -0.013400
 0.770000 -0.011800
 0.780000 -0.010200
 0.790000 -0.008700
 0.800000 -0.007200
 0.810000 -0.005800
 0.820000 -0.004400
 0.830000 -0.003100
 0.840000 -0.001800
 0.850000 -0.000600
 0.860000  0.000500
 0.870000  0.001500
 0.880000  0.002400
 0.890000  0.003100
 0.900000  0.003700
 0.910000  0.004100
 0.920000  0.004300
 0.930000  0.004300
 0.940000  0.004100
 0.950000  0.003700
 0.960000  0.003100
 0.970000  0.002300
 0.980000  0.001200
 0.990000 -0.000100
 1.000000 -0.001700
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Polars for NASA SC(2)-0410 AIRFOIL (sc20410-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20410-il50,000922.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20410-il50,000522.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20410-il100,000930.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20410-il100,000529.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20410-il200,000935.3 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20410-il200,000541.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20410-il500,000954 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20410-il500,000560.5 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20410-il1,000,000971.9 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20410-il1,000,000574.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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