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NASA SC(2)-0012 AIRFOIL (sc20012-il)

NASA SC(2)-0012 AIRFOIL - NASA SC(2)-0012 airfoil (NASA TP-2969)


Airfoil sc20012-il
Details Dat file Parser  
(sc20012-il) NASA SC(2)-0012 AIRFOIL
NASA SC(2)-0012 airfoil (NASA TP-2969)
Max thickness 12% 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)-0012 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.009120
 0.005000  0.013920
 0.010000  0.018600
 0.020000  0.024840
 0.030000  0.029160
 0.040000  0.032400
 0.050000  0.035040
 0.060000  0.037320
 0.070000  0.039390
 0.080000  0.041190
 0.090000  0.042820
 0.100000  0.044280
 0.110000  0.045600
 0.120000  0.046800
 0.130000  0.048000
 0.140000  0.049080
 0.150000  0.050040
 0.160000  0.051000
 0.170000  0.051840
 0.180000  0.052680
 0.190000  0.053400
 0.200000  0.054120
 0.210000  0.054720
 0.220000  0.055320
 0.230000  0.055920
 0.240000  0.056400
 0.250000  0.056880
 0.260000  0.057360
 0.270000  0.057720
 0.280000  0.058080
 0.290000  0.058440
 0.300000  0.058800
 0.310000  0.059040
 0.320000  0.059280
 0.330000  0.059520
 0.340000  0.059640
 0.350000  0.059760
 0.360000  0.059880
 0.370000  0.060000
 0.380000  0.060000
 0.390000  0.060000
 0.400000  0.060000
 0.410000  0.060000
 0.420000  0.059880
 0.430000  0.059760
 0.440000  0.059640
 0.450000  0.059520
 0.460000  0.059280
 0.470000  0.059040
 0.480000  0.058800
 0.490000  0.058440
 0.500000  0.058080
 0.510000  0.057720
 0.520000  0.057360
 0.530000  0.056880
 0.540000  0.056400
 0.550000  0.055800
 0.560000  0.055200
 0.570000  0.054600
 0.580000  0.053880
 0.590000  0.053160
 0.600000  0.052320
 0.610000  0.051360
 0.620000  0.050400
 0.630000  0.049320
 0.640000  0.048240
 0.650000  0.047040
 0.660000  0.045840
 0.670000  0.044580
 0.680000  0.043320
 0.690000  0.042060
 0.700000  0.040800
 0.710000  0.039540
 0.720000  0.038280
 0.730000  0.037020
 0.740000  0.035760
 0.750000  0.034500
 0.760000  0.033240
 0.770000  0.031980
 0.780000  0.030720
 0.790000  0.029460
 0.800000  0.028200
 0.810000  0.026940
 0.820000  0.025680
 0.830000  0.024420
 0.840000  0.023160
 0.850000  0.021900
 0.860000  0.020640
 0.870000  0.019380
 0.880000  0.018120
 0.890000  0.016860
 0.900000  0.015600
 0.910000  0.014340
 0.920000  0.013080
 0.930000  0.011820
 0.940000  0.010560
 0.950000  0.009300
 0.960000  0.008040
 0.970000  0.006780
 0.980000  0.005520
 0.990000  0.004260
 1.000000  0.003000

 0.000000  0.000000
 0.002000 -0.009120
 0.005000 -0.013920
 0.010000 -0.018600
 0.020000 -0.024840
 0.030000 -0.029160
 0.040000 -0.032400
 0.050000 -0.035040
 0.060000 -0.037320
 0.070000 -0.039390
 0.080000 -0.041190
 0.090000 -0.042820
 0.100000 -0.044280
 0.110000 -0.045600
 0.120000 -0.046800
 0.130000 -0.048000
 0.140000 -0.049080
 0.150000 -0.050040
 0.160000 -0.051000
 0.170000 -0.051840
 0.180000 -0.052680
 0.190000 -0.053400
 0.200000 -0.054120
 0.210000 -0.054720
 0.220000 -0.055320
 0.230000 -0.055920
 0.240000 -0.056400
 0.250000 -0.056880
 0.260000 -0.057360
 0.270000 -0.057720
 0.280000 -0.058080
 0.290000 -0.058440
 0.300000 -0.058800
 0.310000 -0.059040
 0.320000 -0.059280
 0.330000 -0.059520
 0.340000 -0.059640
 0.350000 -0.059760
 0.360000 -0.059880
 0.370000 -0.060000
 0.380000 -0.060000
 0.390000 -0.060000
 0.400000 -0.060000
 0.410000 -0.060000
 0.420000 -0.059880
 0.430000 -0.059760
 0.440000 -0.059640
 0.450000 -0.059520
 0.460000 -0.059280
 0.470000 -0.059040
 0.480000 -0.058800
 0.490000 -0.058440
 0.500000 -0.058080
 0.510000 -0.057720
 0.520000 -0.057360
 0.530000 -0.056880
 0.540000 -0.056400
 0.550000 -0.055800
 0.560000 -0.055200
 0.570000 -0.054600
 0.580000 -0.053880
 0.590000 -0.053160
 0.600000 -0.052320
 0.610000 -0.051360
 0.620000 -0.050400
 0.630000 -0.049320
 0.640000 -0.048240
 0.650000 -0.047040
 0.660000 -0.045840
 0.670000 -0.044580
 0.680000 -0.043320
 0.690000 -0.042060
 0.700000 -0.040800
 0.710000 -0.039540
 0.720000 -0.038280
 0.730000 -0.037020
 0.740000 -0.035760
 0.750000 -0.034500
 0.760000 -0.033240
 0.770000 -0.031980
 0.780000 -0.030720
 0.790000 -0.029460
 0.800000 -0.028200
 0.810000 -0.026940
 0.820000 -0.025680
 0.830000 -0.024420
 0.840000 -0.023160
 0.850000 -0.021900
 0.860000 -0.020640
 0.870000 -0.019380
 0.880000 -0.018120
 0.890000 -0.016860
 0.900000 -0.015600
 0.910000 -0.014340
 0.920000 -0.013080
 0.930000 -0.011820
 0.940000 -0.010560
 0.950000 -0.009300
 0.960000 -0.008040
 0.970000 -0.006780
 0.980000 -0.005520
 0.990000 -0.004260
 1.000000 -0.003000
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Polars for NASA SC(2)-0012 AIRFOIL (sc20012-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20012-il50,000924.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20012-il50,000523.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20012-il100,000933.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20012-il100,000529.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20012-il200,000936 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20012-il200,000539.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20012-il500,000953.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20012-il500,000558.6 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20012-il1,000,000971.8 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20012-il1,000,000572.9 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
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