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NASA SC(2)-1010 AIRFOIL (sc21010-il)

NASA SC(2)-1010 AIRFOIL - NASA SC(2)-1010 airfoil


Airfoil sc21010-il
Details Dat file Parser  
(sc21010-il) NASA SC(2)-1010 AIRFOIL
NASA SC(2)-1010 airfoil
Max thickness 10% at 32% chord.
Max camber 2.8% at 71% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-1010 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.007600
 0.005000  0.011600
 0.010000  0.015600
 0.020000  0.020700
 0.030000  0.024200
 0.040000  0.027000
 0.050000  0.029400
 0.060000  0.031500
 0.070000  0.033300
 0.080000  0.034900
 0.090000  0.036400
 0.100000  0.037800
 0.110000  0.039000
 0.120000  0.040100
 0.130000  0.041200
 0.140000  0.042200
 0.150000  0.043100
 0.160000  0.043900
 0.170000  0.044700
 0.180000  0.045400
 0.190000  0.046000
 0.200000  0.046600
 0.210000  0.047100
 0.220000  0.047600
 0.230000  0.048000
 0.240000  0.048400
 0.250000  0.048700
 0.260000  0.049000
 0.270000  0.049300
 0.280000  0.049500
 0.290000  0.049700
 0.300000  0.049800
 0.310000  0.049900
 0.320000  0.050000
 0.330000  0.050000
 0.340000  0.050000
 0.350000  0.050000
 0.360000  0.049900
 0.370000  0.049800
 0.380000  0.049700
 0.390000  0.049500
 0.400000  0.049300
 0.410000  0.049100
 0.420000  0.048800
 0.430000  0.048500
 0.440000  0.048200
 0.450000  0.047800
 0.460000  0.047400
 0.470000  0.047000
 0.480000  0.046500
 0.490000  0.046000
 0.500000  0.045500
 0.510000  0.044900
 0.520000  0.044300
 0.530000  0.043700
 0.540000  0.043000
 0.550000  0.042300
 0.560000  0.041600
 0.570000  0.040800
 0.580000  0.040000
 0.590000  0.039100
 0.600000  0.038200
 0.610000  0.037300
 0.620000  0.036300
 0.630000  0.035300
 0.640000  0.034200
 0.650000  0.033000
 0.660000  0.031800
 0.670000  0.030500
 0.680000  0.029200
 0.690000  0.027800
 0.700000  0.026400
 0.710000  0.024900
 0.720000  0.023300
 0.730000  0.021700
 0.740000  0.020000
 0.750000  0.018300
 0.760000  0.016500
 0.770000  0.014700
 0.780000  0.012800
 0.790000  0.010900
 0.800000  0.008900
 0.810000  0.006900
 0.820000  0.004800
 0.830000  0.002700
 0.840000  0.000500
 0.850000 -0.001700
 0.860000 -0.004000
 0.870000 -0.006300
 0.880000 -0.008700
 0.890000 -0.011100
 0.900000 -0.013600
 0.910000 -0.016100
 0.920000 -0.018700
 0.930000 -0.021400
 0.940000 -0.024100
 0.950000 -0.026900
 0.960000 -0.029800
 0.970000 -0.032700
 0.980000 -0.035700
 0.990000 -0.038800
 1.000000 -0.042000

 0.000000  0.000000
 0.002000 -0.007600
 0.005000 -0.011600
 0.010000 -0.015600
 0.020000 -0.020700
 0.030000 -0.024200
 0.040000 -0.027000
 0.050000 -0.029400
 0.060000 -0.031400
 0.070000 -0.033200
 0.080000 -0.034800
 0.090000 -0.036200
 0.100000 -0.037500
 0.110000 -0.038700
 0.120000 -0.039800
 0.130000 -0.040800
 0.140000 -0.041800
 0.150000 -0.042700
 0.160000 -0.043500
 0.170000 -0.044300
 0.180000 -0.045000
 0.190000 -0.045700
 0.200000 -0.046300
 0.210000 -0.046800
 0.220000 -0.047300
 0.230000 -0.047800
 0.240000 -0.048200
 0.250000 -0.048600
 0.260000 -0.048900
 0.270000 -0.049200
 0.280000 -0.049400
 0.290000 -0.049600
 0.300000 -0.049800
 0.310000 -0.049900
 0.320000 -0.050000
 0.330000 -0.050000
 0.340000 -0.050000
 0.350000 -0.050000
 0.360000 -0.049900
 0.370000 -0.049800
 0.380000 -0.049600
 0.390000 -0.049400
 0.400000 -0.049200
 0.410000 -0.048900
 0.420000 -0.048600
 0.430000 -0.048300
 0.440000 -0.048000
 0.450000 -0.047600
 0.460000 -0.047200
 0.470000 -0.046800
 0.480000 -0.046400
 0.490000 -0.045900
 0.500000 -0.045400
 0.510000 -0.044900
 0.520000 -0.044400
 0.530000 -0.043900
 0.540000 -0.043400
 0.550000 -0.042800
 0.560000 -0.042200
 0.570000 -0.041600
 0.580000 -0.041000
 0.590000 -0.040400
 0.600000 -0.039800
 0.610000 -0.039200
 0.620000 -0.038600
 0.630000 -0.038000
 0.640000 -0.037400
 0.650000 -0.036700
 0.660000 -0.036000
 0.670000 -0.035300
 0.680000 -0.034600
 0.690000 -0.033900
 0.700000 -0.033200
 0.710000 -0.032500
 0.720000 -0.031900
 0.730000 -0.031300
 0.740000 -0.030700
 0.750000 -0.030100
 0.760000 -0.029500
 0.770000 -0.029000
 0.780000 -0.028500
 0.790000 -0.028000
 0.800000 -0.027600
 0.810000 -0.027200
 0.820000 -0.026900
 0.830000 -0.026600
 0.840000 -0.026400
 0.850000 -0.026300
 0.860000 -0.026400
 0.870000 -0.026700
 0.880000 -0.027100
 0.890000 -0.027700
 0.900000 -0.028500
 0.910000 -0.029500
 0.920000 -0.030700
 0.930000 -0.032100
 0.940000 -0.033700
 0.950000 -0.035500
 0.960000 -0.037500
 0.970000 -0.039800
 0.980000 -0.042300
 0.990000 -0.045100
 1.000000 -0.048100
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Polars for NASA SC(2)-1010 AIRFOIL (sc21010-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc21010-il50,000932.1 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21010-il50,000536.1 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21010-il100,000948.7 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21010-il100,000549.6 at α=0.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21010-il200,000969.3 at α=0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21010-il200,000567.7 at α=-0.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21010-il500,0009100.8 at α=-0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21010-il500,000585.6 at α=-1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc21010-il1,000,0009115.3 at α=-1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc21010-il1,000,000589.9 at α=-2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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