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NASA SC(2)-0402 AIRFOIL (sc20402-il)

NASA SC(2)-0402 AIRFOIL - NASA SC(2)-0402 airfoil (NASA TP-2969)


Airfoil sc20402-il
Details Dat file Parser  
(sc20402-il) NASA SC(2)-0402 AIRFOIL
NASA SC(2)-0402 airfoil (NASA TP-2969)
Max thickness 2% at 34% chord.
Max camber 0.5% at 83% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0402 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.001350
 0.005000  0.002050
 0.010000  0.002800
 0.020000  0.003750
 0.030000  0.004450
 0.040000  0.005000
 0.050000  0.005500
 0.060000  0.005900
 0.070000  0.006250
 0.080000  0.006600
 0.090000  0.006900
 0.100000  0.007200
 0.110000  0.007450
 0.120000  0.007700
 0.130000  0.007900
 0.140000  0.008100
 0.150000  0.008300
 0.160000  0.008450
 0.170000  0.008600
 0.180000  0.008750
 0.190000  0.008900
 0.200000  0.009000
 0.210000  0.009100
 0.220000  0.009200
 0.230000  0.009300
 0.240000  0.009400
 0.250000  0.009500
 0.260000  0.009600
 0.270000  0.009650
 0.280000  0.009700
 0.290000  0.009750
 0.300000  0.009800
 0.310000  0.009850
 0.320000  0.009900
 0.330000  0.009950
 0.340000  0.010000
 0.350000  0.010000
 0.360000  0.010000
 0.370000  0.010000
 0.380000  0.010000
 0.390000  0.010000
 0.400000  0.010000
 0.410000  0.010000
 0.420000  0.010000
 0.430000  0.010000
 0.440000  0.010000
 0.450000  0.009950
 0.460000  0.009900
 0.470000  0.009850
 0.480000  0.009800
 0.490000  0.009750
 0.500000  0.009700
 0.510000  0.009650
 0.520000  0.009600
 0.530000  0.009550
 0.540000  0.009500
 0.550000  0.009400
 0.560000  0.009300
 0.570000  0.009200
 0.580000  0.009100
 0.590000  0.009000
 0.600000  0.008900
 0.610000  0.008800
 0.620000  0.008700
 0.630000  0.008600
 0.640000  0.008450
 0.650000  0.008300
 0.660000  0.008150
 0.670000  0.008000
 0.680000  0.007850
 0.690000  0.007700
 0.700000  0.007550
 0.710000  0.007400
 0.720000  0.007200
 0.730000  0.007000
 0.740000  0.006800
 0.750000  0.006600
 0.760000  0.006400
 0.770000  0.006200
 0.780000  0.006000
 0.790000  0.005800
 0.800000  0.005550
 0.810000  0.005300
 0.820000  0.005050
 0.830000  0.004800
 0.840000  0.004550
 0.850000  0.004250
 0.860000  0.003950
 0.870000  0.003650
 0.880000  0.003300
 0.890000  0.002950
 0.900000  0.002550
 0.910000  0.002150
 0.920000  0.001700
 0.930000  0.001200
 0.940000  0.000700
 0.950000  0.000150
 0.960000 -0.000450
 0.970000 -0.001100
 0.980000 -0.001800
 0.990000 -0.002650
 1.000000 -0.003600

 0.000000  0.000000
 0.002000 -0.001350
 0.005000 -0.002050
 0.010000 -0.002800
 0.020000 -0.003750
 0.030000 -0.004450
 0.040000 -0.005000
 0.050000 -0.005500
 0.060000 -0.005900
 0.070000 -0.006250
 0.080000 -0.006600
 0.090000 -0.006900
 0.100000 -0.007200
 0.110000 -0.007450
 0.120000 -0.007700
 0.130000 -0.007900
 0.140000 -0.008100
 0.150000 -0.008300
 0.160000 -0.008450
 0.170000 -0.008600
 0.180000 -0.008750
 0.190000 -0.008900
 0.200000 -0.009000
 0.210000 -0.009100
 0.220000 -0.009200
 0.230000 -0.009300
 0.240000 -0.009400
 0.250000 -0.009500
 0.260000 -0.009600
 0.270000 -0.009650
 0.280000 -0.009700
 0.290000 -0.009750
 0.300000 -0.009800
 0.310000 -0.009850
 0.320000 -0.009900
 0.330000 -0.009950
 0.340000 -0.009950
 0.350000 -0.009950
 0.360000 -0.009950
 0.370000 -0.009950
 0.380000 -0.009950
 0.390000 -0.009950
 0.400000 -0.009950
 0.410000 -0.009900
 0.420000 -0.009850
 0.430000 -0.009800
 0.440000 -0.009750
 0.450000 -0.009650
 0.460000 -0.009550
 0.470000 -0.009450
 0.480000 -0.009350
 0.490000 -0.009250
 0.500000 -0.009150
 0.510000 -0.009000
 0.520000 -0.008850
 0.530000 -0.008700
 0.540000 -0.008550
 0.550000 -0.008400
 0.560000 -0.008200
 0.570000 -0.008000
 0.580000 -0.007800
 0.590000 -0.007600
 0.600000 -0.007350
 0.610000 -0.007100
 0.620000 -0.006850
 0.630000 -0.006600
 0.640000 -0.006350
 0.650000 -0.006100
 0.660000 -0.005850
 0.670000 -0.005600
 0.680000 -0.005350
 0.690000 -0.005100
 0.700000 -0.004850
 0.710000 -0.004600
 0.720000 -0.004350
 0.730000 -0.004100
 0.740000 -0.003850
 0.750000 -0.003600
 0.760000 -0.003350
 0.770000 -0.003100
 0.780000 -0.002850
 0.790000 -0.002600
 0.800000 -0.002400
 0.810000 -0.002200
 0.820000 -0.002000
 0.830000 -0.001800
 0.840000 -0.001650
 0.850000 -0.001550
 0.860000 -0.001450
 0.870000 -0.001400
 0.880000 -0.001400
 0.890000 -0.001400
 0.900000 -0.001500
 0.910000 -0.001600
 0.920000 -0.001750
 0.930000 -0.001950
 0.940000 -0.002200
 0.950000 -0.002500
 0.960000 -0.002900
 0.970000 -0.003400
 0.980000 -0.004000
 0.990000 -0.004700
 1.000000 -0.005500
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Polars for NASA SC(2)-0402 AIRFOIL (sc20402-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20402-il50,000914.2 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20402-il50,000514.5 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20402-il100,000916.3 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20402-il100,000516.9 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20402-il200,000920.1 at α=0.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20402-il200,000540.1 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20402-il500,000064.6 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20402-il1,000,000932.7 at α=-0.25°Mach=0 Ncrit=9Xfoil predictionDetails
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