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NASA SC(2)-0610 AIRFOIL (sc20610-il)

NASA SC(2)-0610 AIRFOIL - NASA SC(2)-0610 airfoil (NASA TP-2969)


Airfoil sc20610-il
Details Dat file Parser  
(sc20610-il) NASA SC(2)-0610 AIRFOIL
NASA SC(2)-0610 airfoil (NASA TP-2969)
Max thickness 10% at 38% chord.
Max camber 1.8% at 82% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0610 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.007600
 0.005000  0.011600
 0.010000  0.015500
 0.020000  0.020600
 0.030000  0.024100
 0.040000  0.026800
 0.050000  0.029000
 0.060000  0.030900
 0.070000  0.032600
 0.080000  0.034100
 0.090000  0.035500
 0.100000  0.036700
 0.110000  0.037800
 0.120000  0.038900
 0.130000  0.039900
 0.140000  0.040800
 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  0.048900
 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  0.049900
 0.440000  0.049800
 0.450000  0.049700
 0.460000  0.049600
 0.470000  0.049400
 0.480000  0.049200
 0.490000  0.049000
 0.500000  0.048800
 0.510000  0.048600
 0.520000  0.048300
 0.530000  0.048000
 0.540000  0.047700
 0.550000  0.047400
 0.560000  0.047000
 0.570000  0.046600
 0.580000  0.046200
 0.590000  0.045800
 0.600000  0.045300
 0.610000  0.044800
 0.620000  0.044300
 0.630000  0.043800
 0.640000  0.043200
 0.650000  0.042600
 0.660000  0.041900
 0.670000  0.041200
 0.680000  0.040500
 0.690000  0.039700
 0.700000  0.038900
 0.710000  0.038100
 0.720000  0.037200
 0.730000  0.036300
 0.740000  0.035300
 0.750000  0.034300
 0.760000  0.033200
 0.770000  0.032100
 0.780000  0.030900
 0.790000  0.029700
 0.800000  0.028500
 0.810000  0.027200
 0.820000  0.025900
 0.830000  0.024500
 0.840000  0.023100
 0.850000  0.021600
 0.860000  0.020100
 0.870000  0.018500
 0.880000  0.016900
 0.890000  0.015300
 0.900000  0.013600
 0.910000  0.011900
 0.920000  0.010100
 0.930000  0.008300
 0.940000  0.006400
 0.950000  0.004500
 0.960000  0.002500
 0.970000  0.000400
 0.980000 -0.001800
 0.990000 -0.004200
 1.000000 -0.006700

 0.000000  0.000000
 0.002000 -0.007600
 0.005000 -0.011600
 0.010000 -0.015500
 0.020000 -0.020600
 0.030000 -0.024100
 0.040000 -0.026800
 0.050000 -0.029000
 0.060000 -0.030900
 0.070000 -0.032600
 0.080000 -0.034100
 0.090000 -0.035500
 0.100000 -0.036700
 0.110000 -0.037900
 0.120000 -0.039000
 0.130000 -0.040000
 0.140000 -0.040900
 0.150000 -0.041800
 0.160000 -0.042600
 0.170000 -0.043300
 0.180000 -0.044000
 0.190000 -0.044600
 0.200000 -0.045200
 0.210000 -0.045800
 0.220000 -0.046300
 0.230000 -0.046800
 0.240000 -0.047200
 0.250000 -0.047600
 0.260000 -0.048000
 0.270000 -0.048300
 0.280000 -0.048600
 0.290000 -0.048900
 0.300000 -0.049100
 0.310000 -0.049300
 0.320000 -0.049500
 0.330000 -0.049600
 0.340000 -0.049700
 0.350000 -0.049800
 0.360000 -0.049800
 0.370000 -0.049800
 0.380000 -0.049800
 0.390000 -0.049700
 0.400000 -0.049600
 0.410000 -0.049500
 0.420000 -0.049300
 0.430000 -0.049100
 0.440000 -0.048900
 0.450000 -0.048600
 0.460000 -0.048300
 0.470000 -0.047900
 0.480000 -0.047500
 0.490000 -0.047000
 0.500000 -0.046500
 0.510000 -0.045900
 0.520000 -0.045300
 0.530000 -0.044600
 0.540000 -0.043900
 0.550000 -0.043100
 0.560000 -0.042200
 0.570000 -0.041200
 0.580000 -0.040100
 0.590000 -0.039000
 0.600000 -0.037800
 0.610000 -0.036600
 0.620000 -0.035300
 0.630000 -0.034000
 0.640000 -0.032700
 0.650000 -0.031300
 0.660000 -0.029900
 0.670000 -0.028400
 0.680000 -0.026900
 0.690000 -0.025400
 0.700000 -0.023800
 0.710000 -0.022200
 0.720000 -0.020600
 0.730000 -0.019000
 0.740000 -0.017400
 0.750000 -0.015800
 0.760000 -0.014200
 0.770000 -0.012600
 0.780000 -0.011100
 0.790000 -0.009600
 0.800000 -0.008100
 0.810000 -0.006800
 0.820000 -0.005600
 0.830000 -0.004500
 0.840000 -0.003500
 0.850000 -0.002600
 0.860000 -0.001800
 0.870000 -0.001200
 0.880000 -0.000700
 0.890000 -0.000400
 0.900000 -0.000300
 0.910000 -0.000400
 0.920000 -0.000700
 0.930000 -0.001200
 0.940000 -0.002000
 0.950000 -0.003000
 0.960000 -0.004200
 0.970000 -0.005600
 0.980000 -0.007300
 0.990000 -0.009300
 1.000000 -0.011600
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Polars for NASA SC(2)-0610 AIRFOIL (sc20610-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20610-il50,000923.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20610-il50,000524.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20610-il100,000931.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20610-il100,000531.8 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20610-il200,000941.9 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20610-il200,000543.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20610-il500,000964.9 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20610-il500,000562.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20610-il1,000,000974.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20610-il1,000,000577.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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