NASA SC(2)-0414 AIRFOIL (sc20414-il)
NASA SC(2)-0414 AIRFOIL - NASA SC(2)-0414 airfoil (NASA TP-2969)
| Details | Dat file | Parser | |
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20414-il | 50,000 | 9 | 25.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 50,000 | 5 | 21.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 100,000 | 9 | 25.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 100,000 | 5 | 30.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 200,000 | 9 | 35.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 200,000 | 5 | 43.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 500,000 | 9 | 57.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 500,000 | 5 | 63.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20414-il | 1,000,000 | 9 | 76.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20414-il | 1,000,000 | 5 | 78.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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