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NASA SC(2)-0010 AIRFOIL (sc20010-il)

NASA SC(2)-0010 AIRFOIL - NASA SC(2)-0010 airfoil (NASA TP-2969)


Airfoil sc20010-il
Details Dat file Parser  
(sc20010-il) NASA SC(2)-0010 AIRFOIL
NASA SC(2)-0010 airfoil (NASA TP-2969)
Max thickness 10% at 37% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0010 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  0.024300
 0.040000  0.027000
 0.050000  0.029200
 0.060000  0.031100
 0.070000  0.032800
 0.080000  0.034300
 0.090000  0.035700
 0.100000  0.036900
 0.110000  0.038000
 0.120000  0.039000
 0.130000  0.040000
 0.140000  0.040900
 0.150000  0.041700
 0.160000  0.042500
 0.170000  0.043200
 0.180000  0.043900
 0.190000  0.044500
 0.200000  0.045100
 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  0.049000
 0.310000  0.049200
 0.320000  0.049400
 0.330000  0.049600
 0.340000  0.049700
 0.350000  0.049800
 0.360000  0.049900
 0.370000  0.050000
 0.380000  0.050000
 0.390000  0.050000
 0.400000  0.050000
 0.410000  0.050000
 0.420000  0.049900
 0.430000  0.049800
 0.440000  0.049700
 0.450000  0.049600
 0.460000  0.049400
 0.470000  0.049200
 0.480000  0.049000
 0.490000  0.048700
 0.500000  0.048400
 0.510000  0.048100
 0.520000  0.047800
 0.530000  0.047400
 0.540000  0.047000
 0.550000  0.046500
 0.560000  0.046000
 0.570000  0.045500
 0.580000  0.044900
 0.590000  0.044300
 0.600000  0.043600
 0.610000  0.042800
 0.620000  0.042000
 0.630000  0.041100
 0.640000  0.040200
 0.650000  0.039200
 0.660000  0.038200
 0.670000  0.037150
 0.680000  0.036100
 0.690000  0.035050
 0.700000  0.034000
 0.710000  0.032950
 0.720000  0.031900
 0.730000  0.030850
 0.740000  0.029800
 0.750000  0.028750
 0.760000  0.027700
 0.770000  0.026650
 0.780000  0.025600
 0.790000  0.024550
 0.800000  0.023500
 0.810000  0.022450
 0.820000  0.021400
 0.830000  0.020350
 0.840000  0.019300
 0.850000  0.018250
 0.860000  0.017200
 0.870000  0.016150
 0.880000  0.015100
 0.890000  0.014050
 0.900000  0.013000
 0.910000  0.011950
 0.920000  0.010900
 0.930000  0.009850
 0.940000  0.008800
 0.950000  0.007750
 0.960000  0.006700
 0.970000  0.005650
 0.980000  0.004600
 0.990000  0.003550
 1.000000  0.002500

 0.000000  0.000000
 0.002000 -0.007600
 0.005000 -0.011600
 0.010000 -0.015500
 0.020000 -0.020700
 0.030000 -0.024300
 0.040000 -0.027000
 0.050000 -0.029200
 0.060000 -0.031100
 0.070000 -0.032800
 0.080000 -0.034300
 0.090000 -0.035700
 0.100000 -0.036900
 0.110000 -0.038000
 0.120000 -0.039000
 0.130000 -0.040000
 0.140000 -0.040900
 0.150000 -0.041700
 0.160000 -0.042500
 0.170000 -0.043200
 0.180000 -0.043900
 0.190000 -0.044500
 0.200000 -0.045100
 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 -0.049000
 0.310000 -0.049200
 0.320000 -0.049400
 0.330000 -0.049600
 0.340000 -0.049700
 0.350000 -0.049800
 0.360000 -0.049900
 0.370000 -0.050000
 0.380000 -0.050000
 0.390000 -0.050000
 0.400000 -0.050000
 0.410000 -0.050000
 0.420000 -0.049900
 0.430000 -0.049800
 0.440000 -0.049700
 0.450000 -0.049600
 0.460000 -0.049400
 0.470000 -0.049200
 0.480000 -0.049000
 0.490000 -0.048700
 0.500000 -0.048400
 0.510000 -0.048100
 0.520000 -0.047800
 0.530000 -0.047400
 0.540000 -0.047000
 0.550000 -0.046500
 0.560000 -0.046000
 0.570000 -0.045500
 0.580000 -0.044900
 0.590000 -0.044300
 0.600000 -0.043600
 0.610000 -0.042800
 0.620000 -0.042000
 0.630000 -0.041100
 0.640000 -0.040200
 0.650000 -0.039200
 0.660000 -0.038200
 0.670000 -0.037150
 0.680000 -0.036100
 0.690000 -0.035050
 0.700000 -0.034000
 0.710000 -0.032950
 0.720000 -0.031900
 0.730000 -0.030850
 0.740000 -0.029800
 0.750000 -0.028750
 0.760000 -0.027700
 0.770000 -0.026650
 0.780000 -0.025600
 0.790000 -0.024550
 0.800000 -0.023500
 0.810000 -0.022450
 0.820000 -0.021400
 0.830000 -0.020350
 0.840000 -0.019300
 0.850000 -0.018250
 0.860000 -0.017200
 0.870000 -0.016150
 0.880000 -0.015100
 0.890000 -0.014050
 0.900000 -0.013000
 0.910000 -0.011950
 0.920000 -0.010900
 0.930000 -0.009850
 0.940000 -0.008800
 0.950000 -0.007750
 0.960000 -0.006700
 0.970000 -0.005650
 0.980000 -0.004600
 0.990000 -0.003550
 1.000000 -0.002500
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Lednicer format dat file
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Polars for NASA SC(2)-0010 AIRFOIL (sc20010-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20010-il50,000923.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20010-il50,000522.9 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20010-il100,000933.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20010-il100,000528.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20010-il200,000939.5 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20010-il200,000539 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20010-il500,000952 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20010-il500,000556.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20010-il1,000,000967.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20010-il1,000,000570.1 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
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