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NASA SC(2)-0412 AIRFOIL (sc20412-il)

NASA SC(2)-0412 AIRFOIL - NASA SC(2)-0412 airfoil (NASA TP-2969)


Airfoil sc20412-il
Details Dat file Parser  
(sc20412-il) NASA SC(2)-0412 AIRFOIL
NASA SC(2)-0412 airfoil (NASA TP-2969)
Max thickness 12% at 37% chord.
Max camber 1.3% at 83% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0412 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.009200
 0.005000  0.014100
 0.010000  0.019000
 0.020000  0.025300
 0.030000  0.029700
 0.040000  0.033000
 0.050000  0.035700
 0.060000  0.038000
 0.070000  0.040000
 0.080000  0.041800
 0.090000  0.043400
 0.100000  0.044800
 0.110000  0.046100
 0.120000  0.047300
 0.130000  0.048400
 0.140000  0.049400
 0.150000  0.050400
 0.160000  0.051300
 0.170000  0.052200
 0.180000  0.053000
 0.190000  0.053700
 0.200000  0.054400
 0.210000  0.055000
 0.220000  0.055600
 0.230000  0.056200
 0.240000  0.056700
 0.250000  0.057100
 0.260000  0.057500
 0.270000  0.057900
 0.280000  0.058300
 0.290000  0.058600
 0.300000  0.058900
 0.310000  0.059100
 0.320000  0.059300
 0.330000  0.059500
 0.340000  0.059700
 0.350000  0.059800
 0.360000  0.059900
 0.370000  0.060000
 0.380000  0.060100
 0.390000  0.060100
 0.400000  0.060100
 0.410000  0.060100
 0.420000  0.060100
 0.430000  0.060000
 0.440000  0.059900
 0.450000  0.059800
 0.460000  0.059700
 0.470000  0.059500
 0.480000  0.059300
 0.490000  0.059100
 0.500000  0.058800
 0.510000  0.058500
 0.520000  0.058200
 0.530000  0.057800
 0.540000  0.057400
 0.550000  0.057000
 0.560000  0.056500
 0.570000  0.056000
 0.580000  0.055500
 0.590000  0.054900
 0.600000  0.054300
 0.610000  0.053600
 0.620000  0.052900
 0.630000  0.052200
 0.640000  0.051400
 0.650000  0.050600
 0.660000  0.049700
 0.670000  0.048800
 0.680000  0.047900
 0.690000  0.046900
 0.700000  0.045900
 0.710000  0.044900
 0.720000  0.043900
 0.730000  0.042800
 0.740000  0.041700
 0.750000  0.040600
 0.760000  0.039400
 0.770000  0.038200
 0.780000  0.037000
 0.790000  0.035800
 0.800000  0.034500
 0.810000  0.033200
 0.820000  0.031900
 0.830000  0.030600
 0.840000  0.029200
 0.850000  0.027800
 0.860000  0.026400
 0.870000  0.025000
 0.880000  0.023500
 0.890000  0.022000
 0.900000  0.020500
 0.910000  0.019000
 0.920000  0.017400
 0.930000  0.015800
 0.940000  0.014200
 0.950000  0.012500
 0.960000  0.010800
 0.970000  0.009000
 0.980000  0.007200
 0.990000  0.005300
 1.000000  0.003300

 0.000000  0.000000
 0.002000 -0.009200
 0.005000 -0.014100
 0.010000 -0.019000
 0.020000 -0.025300
 0.030000 -0.029600
 0.040000 -0.032900
 0.050000 -0.035600
 0.060000 -0.037900
 0.070000 -0.040000
 0.080000 -0.041800
 0.090000 -0.043400
 0.100000 -0.044900
 0.110000 -0.046300
 0.120000 -0.047600
 0.130000 -0.048800
 0.140000 -0.049900
 0.150000 -0.050900
 0.160000 -0.051800
 0.170000 -0.052700
 0.180000 -0.053500
 0.190000 -0.054200
 0.200000 -0.054900
 0.210000 -0.055500
 0.220000 -0.056100
 0.230000 -0.056700
 0.240000 -0.057200
 0.250000 -0.057700
 0.260000 -0.058100
 0.270000 -0.058500
 0.280000 -0.058800
 0.290000 -0.059100
 0.300000 -0.059300
 0.310000 -0.059500
 0.320000 -0.059700
 0.330000 -0.059800
 0.340000 -0.059900
 0.350000 -0.060000
 0.360000 -0.060000
 0.370000 -0.060000
 0.380000 -0.059900
 0.390000 -0.059800
 0.400000 -0.059600
 0.410000 -0.059400
 0.420000 -0.059200
 0.430000 -0.058900
 0.440000 -0.058600
 0.450000 -0.058200
 0.460000 -0.057800
 0.470000 -0.057300
 0.480000 -0.056800
 0.490000 -0.056200
 0.500000 -0.055500
 0.510000 -0.054700
 0.520000 -0.053900
 0.530000 -0.053000
 0.540000 -0.052000
 0.550000 -0.050900
 0.560000 -0.049800
 0.570000 -0.048600
 0.580000 -0.047300
 0.590000 -0.045900
 0.600000 -0.044400
 0.610000 -0.042900
 0.620000 -0.041300
 0.630000 -0.039700
 0.640000 -0.038000
 0.650000 -0.036200
 0.660000 -0.034400
 0.670000 -0.032600
 0.680000 -0.030700
 0.690000 -0.028800
 0.700000 -0.026900
 0.710000 -0.025000
 0.720000 -0.023100
 0.730000 -0.021200
 0.740000 -0.019300
 0.750000 -0.017400
 0.760000 -0.015500
 0.770000 -0.013700
 0.780000 -0.011900
 0.790000 -0.010200
 0.800000 -0.008500
 0.810000 -0.006800
 0.820000 -0.005200
 0.830000 -0.003700
 0.840000 -0.002300
 0.850000 -0.000900
 0.860000  0.000300
 0.870000  0.001400
 0.880000  0.002400
 0.890000  0.003200
 0.900000  0.003800
 0.910000  0.004300
 0.920000  0.004500
 0.930000  0.004500
 0.940000  0.004200
 0.950000  0.003800
 0.960000  0.003100
 0.970000  0.002200
 0.980000  0.001000
 0.990000 -0.000500
 1.000000 -0.002200
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Polars for NASA SC(2)-0412 AIRFOIL (sc20412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20412-il50,000924.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20412-il50,000521.8 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20412-il100,000926.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20412-il100,000530.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20412-il200,000935.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20412-il200,000543 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20412-il500,000956.7 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20412-il500,000563 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20412-il1,000,000975.8 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20412-il1,000,000578.2 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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