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NASA SC(2)-0414 AIRFOIL (sc20414-il)

NASA SC(2)-0414 AIRFOIL - NASA SC(2)-0414 airfoil (NASA TP-2969)


Airfoil sc20414-il
Details Dat file Parser  
(sc20414-il) NASA SC(2)-0414 AIRFOIL
NASA SC(2)-0414 airfoil (NASA TP-2969)
Max thickness 14% at 36% chord.
Max camber 1.5% at 83% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0414 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.010800
 0.005000  0.016600
 0.010000  0.022500
 0.020000  0.029900
 0.030000  0.035000
 0.040000  0.038900
 0.050000  0.042100
 0.060000  0.044800
 0.070000  0.047100
 0.080000  0.049100
 0.090000  0.051000
 0.100000  0.052700
 0.110000  0.054200
 0.120000  0.055600
 0.130000  0.056900
 0.140000  0.058100
 0.150000  0.059200
 0.160000  0.060200
 0.170000  0.061200
 0.180000  0.062100
 0.190000  0.062900
 0.200000  0.063700
 0.210000  0.064400
 0.220000  0.065100
 0.230000  0.065700
 0.240000  0.066300
 0.250000  0.066800
 0.260000  0.067300
 0.270000  0.067700
 0.280000  0.068100
 0.290000  0.068500
 0.300000  0.068800
 0.310000  0.069100
 0.320000  0.069300
 0.330000  0.069500
 0.340000  0.069700
 0.350000  0.069900
 0.360000  0.070000
 0.370000  0.070100
 0.380000  0.070200
 0.390000  0.070200
 0.400000  0.070200
 0.410000  0.070200
 0.420000  0.070100
 0.430000  0.070000
 0.440000  0.069900
 0.450000  0.069700
 0.460000  0.069500
 0.470000  0.069300
 0.480000  0.069000
 0.490000  0.068700
 0.500000  0.068400
 0.510000  0.068000
 0.520000  0.067600
 0.530000  0.067200
 0.540000  0.066700
 0.550000  0.066200
 0.560000  0.065600
 0.570000  0.065000
 0.580000  0.064300
 0.590000  0.063600
 0.600000  0.062800
 0.610000  0.062000
 0.620000  0.061100
 0.630000  0.060200
 0.640000  0.059300
 0.650000  0.058300
 0.660000  0.057300
 0.670000  0.056200
 0.680000  0.055100
 0.690000  0.054000
 0.700000  0.052800
 0.710000  0.051600
 0.720000  0.050300
 0.730000  0.049000
 0.740000  0.047700
 0.750000  0.046400
 0.760000  0.045000
 0.770000  0.043600
 0.780000  0.042200
 0.790000  0.040700
 0.800000  0.039200
 0.810000  0.037700
 0.820000  0.036200
 0.830000  0.034600
 0.840000  0.033000
 0.850000  0.031400
 0.860000  0.029800
 0.870000  0.028100
 0.880000  0.026400
 0.890000  0.024700
 0.900000  0.022900
 0.910000  0.021100
 0.920000  0.019300
 0.930000  0.017500
 0.940000  0.015600
 0.950000  0.013700
 0.960000  0.011700
 0.970000  0.009700
 0.980000  0.007600
 0.990000  0.005500
 1.000000  0.003300

 0.000000  0.000000
 0.002000 -0.010800
 0.005000 -0.016600
 0.010000 -0.022500
 0.020000 -0.029900
 0.030000 -0.035000
 0.040000 -0.038900
 0.050000 -0.042100
 0.060000 -0.044800
 0.070000 -0.047200
 0.080000 -0.049300
 0.090000 -0.051200
 0.100000 -0.052900
 0.110000 -0.054500
 0.120000 -0.056000
 0.130000 -0.057300
 0.140000 -0.058500
 0.150000 -0.059700
 0.160000 -0.060800
 0.170000 -0.061800
 0.180000 -0.062700
 0.190000 -0.063600
 0.200000 -0.064400
 0.210000 -0.065100
 0.220000 -0.065800
 0.230000 -0.066400
 0.240000 -0.067000
 0.250000 -0.067500
 0.260000 -0.068000
 0.270000 -0.068400
 0.280000 -0.068800
 0.290000 -0.069100
 0.300000 -0.069400
 0.310000 -0.069600
 0.320000 -0.069800
 0.330000 -0.069900
 0.340000 -0.070000
 0.350000 -0.070000
 0.360000 -0.070000
 0.370000 -0.069900
 0.380000 -0.069800
 0.390000 -0.069700
 0.400000 -0.069500
 0.410000 -0.069300
 0.420000 -0.069000
 0.430000 -0.068600
 0.440000 -0.068200
 0.450000 -0.067700
 0.460000 -0.067200
 0.470000 -0.066600
 0.480000 -0.065900
 0.490000 -0.065100
 0.500000 -0.064200
 0.510000 -0.063300
 0.520000 -0.062300
 0.530000 -0.061200
 0.540000 -0.060000
 0.550000 -0.058700
 0.560000 -0.057300
 0.570000 -0.055800
 0.580000 -0.054300
 0.590000 -0.052700
 0.600000 -0.051000
 0.610000 -0.049200
 0.620000 -0.047400
 0.630000 -0.045500
 0.640000 -0.043500
 0.650000 -0.041500
 0.660000 -0.039400
 0.670000 -0.037300
 0.680000 -0.035200
 0.690000 -0.033000
 0.700000 -0.030800
 0.710000 -0.028600
 0.720000 -0.026400
 0.730000 -0.024200
 0.740000 -0.022000
 0.750000 -0.019800
 0.760000 -0.017700
 0.770000 -0.015600
 0.780000 -0.013600
 0.790000 -0.011600
 0.800000 -0.009700
 0.810000 -0.007800
 0.820000 -0.006000
 0.830000 -0.004300
 0.840000 -0.002700
 0.850000 -0.001200
 0.860000  0.000100
 0.870000  0.001300
 0.880000  0.002300
 0.890000  0.003200
 0.900000  0.003900
 0.910000  0.004400
 0.920000  0.004600
 0.930000  0.004600
 0.940000  0.004300
 0.950000  0.003800
 0.960000  0.003100
 0.970000  0.002100
 0.980000  0.000800
 0.990000 -0.000800
 1.000000 -0.002700
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Polars for NASA SC(2)-0414 AIRFOIL (sc20414-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20414-il50,000925.9 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20414-il50,000521.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20414-il100,000925.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20414-il100,000530.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20414-il200,000935.3 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20414-il200,000543.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20414-il500,000957.9 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20414-il500,000563.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20414-il1,000,000976.3 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20414-il1,000,000578.8 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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