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NASA SC(2)-0714 AIRFOIL (sc20714-il)

NASA SC(2)-0714 AIRFOIL - NASA SC(2)-0714 airfoil (NASA TP-2969)


Airfoil sc20714-il
Details Dat file Parser  
(sc20714-il) NASA SC(2)-0714 AIRFOIL
NASA SC(2)-0714 airfoil (NASA TP-2969)
Max thickness 14% at 37% chord.
Max camber 2.5% at 81% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0714 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.010770
 0.005000  0.016580
 0.010000  0.022400
 0.020000  0.029600
 0.030000  0.034600
 0.040000  0.038300
 0.050000  0.041400
 0.060000  0.044000
 0.070000  0.046300
 0.080000  0.048400
 0.090000  0.050200
 0.100000  0.051900
 0.110000  0.053500
 0.120000  0.054900
 0.130000  0.056200
 0.140000  0.057400
 0.150000  0.058600
 0.160000  0.059700
 0.170000  0.060700
 0.180000  0.061600
 0.190000  0.062500
 0.200000  0.063300
 0.210000  0.064100
 0.220000  0.064800
 0.230000  0.065400
 0.240000  0.066000
 0.250000  0.066500
 0.260000  0.067000
 0.270000  0.067500
 0.280000  0.067900
 0.290000  0.068300
 0.300000  0.068600
 0.310000  0.068900
 0.320000  0.069200
 0.330000  0.069400
 0.340000  0.069600
 0.350000  0.069700
 0.360000  0.069800
 0.370000  0.069900
 0.380000  0.069900
 0.390000  0.069900
 0.400000  0.069900
 0.410000  0.069800
 0.420000  0.069700
 0.430000  0.069600
 0.440000  0.069500
 0.450000  0.069300
 0.460000  0.069100
 0.470000  0.068900
 0.480000  0.068600
 0.490000  0.068300
 0.500000  0.068000
 0.510000  0.067600
 0.520000  0.067200
 0.530000  0.066800
 0.540000  0.066300
 0.550000  0.065800
 0.560000  0.065300
 0.570000  0.064700
 0.580000  0.064100
 0.590000  0.063500
 0.600000  0.062800
 0.610000  0.062100
 0.620000  0.061300
 0.630000  0.060500
 0.640000  0.059700
 0.650000  0.058800
 0.660000  0.057900
 0.670000  0.056900
 0.680000  0.055900
 0.690000  0.054800
 0.700000  0.053700
 0.710000  0.052500
 0.720000  0.051300
 0.730000  0.050000
 0.740000  0.048700
 0.750000  0.047300
 0.760000  0.045800
 0.770000  0.044300
 0.780000  0.042700
 0.790000  0.041100
 0.800000  0.039400
 0.810000  0.037600
 0.820000  0.035800
 0.830000  0.033900
 0.840000  0.031900
 0.850000  0.029900
 0.860000  0.027800
 0.870000  0.025600
 0.880000  0.023400
 0.890000  0.021100
 0.900000  0.018700
 0.910000  0.016200
 0.920000  0.013700
 0.930000  0.011100
 0.940000  0.008400
 0.950000  0.005600
 0.960000  0.002700
 0.970000 -0.000200
 0.980000 -0.003200
 0.990000 -0.006300
 1.000000 -0.009500

 0.000000  0.000000
 0.002000 -0.010770
 0.005000 -0.016580
 0.010000 -0.022400
 0.020000 -0.029600
 0.030000 -0.034500
 0.040000 -0.038200
 0.050000 -0.041300
 0.060000 -0.043900
 0.070000 -0.046200
 0.080000 -0.048300
 0.090000 -0.050100
 0.100000 -0.051800
 0.110000 -0.053400
 0.120000 -0.054900
 0.130000 -0.056200
 0.140000 -0.057400
 0.150000 -0.058600
 0.160000 -0.059700
 0.170000 -0.060700
 0.180000 -0.061600
 0.190000 -0.062500
 0.200000 -0.063300
 0.210000 -0.064100
 0.220000 -0.064800
 0.230000 -0.065500
 0.240000 -0.066100
 0.250000 -0.066700
 0.260000 -0.067200
 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 -0.069600
 0.350000 -0.069700
 0.360000 -0.069700
 0.370000 -0.069700
 0.380000 -0.069600
 0.390000 -0.069500
 0.400000 -0.069300
 0.410000 -0.069100
 0.420000 -0.068800
 0.430000 -0.068500
 0.440000 -0.068100
 0.450000 -0.067700
 0.460000 -0.067200
 0.470000 -0.066700
 0.480000 -0.066100
 0.490000 -0.065400
 0.500000 -0.064600
 0.510000 -0.063700
 0.520000 -0.062700
 0.530000 -0.061600
 0.540000 -0.060400
 0.550000 -0.059100
 0.560000 -0.057700
 0.570000 -0.056200
 0.580000 -0.054600
 0.590000 -0.052900
 0.600000 -0.051100
 0.610000 -0.049200
 0.620000 -0.047300
 0.630000 -0.045300
 0.640000 -0.043300
 0.650000 -0.041200
 0.660000 -0.039100
 0.670000 -0.037000
 0.680000 -0.034800
 0.690000 -0.032600
 0.700000 -0.030400
 0.710000 -0.028200
 0.720000 -0.026000
 0.730000 -0.023800
 0.740000 -0.021600
 0.750000 -0.019400
 0.760000 -0.017300
 0.770000 -0.015200
 0.780000 -0.013200
 0.790000 -0.011300
 0.800000 -0.009500
 0.810000 -0.007900
 0.820000 -0.006400
 0.830000 -0.005000
 0.840000 -0.003800
 0.850000 -0.002800
 0.860000 -0.002000
 0.870000 -0.001400
 0.880000 -0.001000
 0.890000 -0.000800
 0.900000 -0.000900
 0.910000 -0.001200
 0.920000 -0.001700
 0.930000 -0.002500
 0.940000 -0.003600
 0.950000 -0.005000
 0.960000 -0.006700
 0.970000 -0.008700
 0.980000 -0.011000
 0.990000 -0.013600
 1.000000 -0.016500
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Polars for NASA SC(2)-0714 AIRFOIL (sc20714-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20714-il50,000925.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20714-il50,000522.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20714-il100,000927.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20714-il100,000531 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20714-il200,000936 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20714-il200,000543.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20714-il500,000963.1 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20714-il500,000564.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20714-il1,000,000981.2 at α=-0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20714-il1,000,000580 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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