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NASA SC(2)-0518 AIRFOIL (sc20518-il)

NASA SC(2)-0518 AIRFOIL - NASA SC(2)-0518 airfoil (NASA TP-2969)


Airfoil sc20518-il
Details Dat file Parser  
(sc20518-il) NASA SC(2)-0518 AIRFOIL
NASA SC(2)-0518 airfoil (NASA TP-2969)
Max thickness 18% at 35% chord.
Max camber 1.9% at 82% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0518 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.013900
 0.005000  0.021300
 0.010000  0.029100
 0.020000  0.038900
 0.030000  0.045600
 0.040000  0.050800
 0.050000  0.055000
 0.060000  0.058500
 0.070000  0.061500
 0.080000  0.064200
 0.090000  0.066600
 0.100000  0.068700
 0.110000  0.070700
 0.120000  0.072500
 0.130000  0.074200
 0.140000  0.075700
 0.150000  0.077100
 0.160000  0.078400
 0.170000  0.079600
 0.180000  0.080700
 0.190000  0.081800
 0.200000  0.082800
 0.210000  0.083700
 0.220000  0.084500
 0.230000  0.085300
 0.240000  0.086000
 0.250000  0.086600
 0.260000  0.087200
 0.270000  0.087700
 0.280000  0.088200
 0.290000  0.088600
 0.300000  0.089000
 0.310000  0.089300
 0.320000  0.089600
 0.330000  0.089800
 0.340000  0.090000
 0.350000  0.090100
 0.360000  0.090200
 0.370000  0.090300
 0.380000  0.090300
 0.390000  0.090300
 0.400000  0.090200
 0.410000  0.090100
 0.420000  0.089900
 0.430000  0.089700
 0.440000  0.089400
 0.450000  0.089100
 0.460000  0.088700
 0.470000  0.088300
 0.480000  0.087800
 0.490000  0.087300
 0.500000  0.086700
 0.510000  0.086000
 0.520000  0.085300
 0.530000  0.084500
 0.540000  0.083700
 0.550000  0.082800
 0.560000  0.081900
 0.570000  0.080900
 0.580000  0.079800
 0.590000  0.078700
 0.600000  0.077500
 0.610000  0.076300
 0.620000  0.075000
 0.630000  0.073700
 0.640000  0.072400
 0.650000  0.071000
 0.660000  0.069600
 0.670000  0.068100
 0.680000  0.066600
 0.690000  0.065000
 0.700000  0.063400
 0.710000  0.061800
 0.720000  0.060100
 0.730000  0.058400
 0.740000  0.056600
 0.750000  0.054800
 0.760000  0.053000
 0.770000  0.051100
 0.780000  0.049200
 0.790000  0.047300
 0.800000  0.045300
 0.810000  0.043300
 0.820000  0.041300
 0.830000  0.039200
 0.840000  0.037100
 0.850000  0.035000
 0.860000  0.032800
 0.870000  0.030600
 0.880000  0.028400
 0.890000  0.026200
 0.900000  0.023900
 0.910000  0.021600
 0.920000  0.019300
 0.930000  0.016900
 0.940000  0.014500
 0.950000  0.012000
 0.960000  0.009400
 0.970000  0.006800
 0.980000  0.004100
 0.990000  0.001400
 1.000000 -0.001400

 0.000000  0.000000
 0.002000 -0.013900
 0.005000 -0.021300
 0.010000 -0.029100
 0.020000 -0.038900
 0.030000 -0.045700
 0.040000 -0.050900
 0.050000 -0.055000
 0.060000 -0.058500
 0.070000 -0.061500
 0.080000 -0.064200
 0.090000 -0.066600
 0.100000 -0.068700
 0.110000 -0.070700
 0.120000 -0.072500
 0.130000 -0.074200
 0.140000 -0.075800
 0.150000 -0.077300
 0.160000 -0.078700
 0.170000 -0.079900
 0.180000 -0.081100
 0.190000 -0.082200
 0.200000 -0.083200
 0.210000 -0.084100
 0.220000 -0.084900
 0.230000 -0.085700
 0.240000 -0.086400
 0.250000 -0.087000
 0.260000 -0.087500
 0.270000 -0.088000
 0.280000 -0.088400
 0.290000 -0.088800
 0.300000 -0.089100
 0.310000 -0.089300
 0.320000 -0.089500
 0.330000 -0.089600
 0.340000 -0.089700
 0.350000 -0.089700
 0.360000 -0.089600
 0.370000 -0.089500
 0.380000 -0.089300
 0.390000 -0.089000
 0.400000 -0.088700
 0.410000 -0.088300
 0.420000 -0.087800
 0.430000 -0.087200
 0.440000 -0.086500
 0.450000 -0.085800
 0.460000 -0.085000
 0.470000 -0.084100
 0.480000 -0.083100
 0.490000 -0.081900
 0.500000 -0.080600
 0.510000 -0.079200
 0.520000 -0.077700
 0.530000 -0.076100
 0.540000 -0.074400
 0.550000 -0.072600
 0.560000 -0.070700
 0.570000 -0.068800
 0.580000 -0.066800
 0.590000 -0.064700
 0.600000 -0.062600
 0.610000 -0.060400
 0.620000 -0.058200
 0.630000 -0.056000
 0.640000 -0.053700
 0.650000 -0.051400
 0.660000 -0.049100
 0.670000 -0.046800
 0.680000 -0.044400
 0.690000 -0.042000
 0.700000 -0.039600
 0.710000 -0.037200
 0.720000 -0.034800
 0.730000 -0.032400
 0.740000 -0.030000
 0.750000 -0.027600
 0.760000 -0.025200
 0.770000 -0.022900
 0.780000 -0.020600
 0.790000 -0.018300
 0.800000 -0.016100
 0.810000 -0.013900
 0.820000 -0.011800
 0.830000 -0.009800
 0.840000 -0.007900
 0.850000 -0.006100
 0.860000 -0.004400
 0.870000 -0.002900
 0.880000 -0.001600
 0.890000 -0.000500
 0.900000  0.000300
 0.910000  0.000900
 0.920000  0.001200
 0.930000  0.001200
 0.940000  0.000900
 0.950000  0.000300
 0.960000 -0.000700
 0.970000 -0.002000
 0.980000 -0.003700
 0.990000 -0.005800
 1.000000 -0.008300
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Polars for NASA SC(2)-0518 AIRFOIL (sc20518-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20518-il50,000926 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20518-il50,000520.9 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20518-il100,000925.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20518-il100,000530.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20518-il200,000936.5 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20518-il200,000543.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20518-il500,000959.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20518-il500,000562.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20518-il1,000,000977.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20518-il1,000,000578.1 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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