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NASA SC(2)-0706 AIRFOIL (sc20706-il)

NASA SC(2)-0706 AIRFOIL - NASA SC(2)-0706 airfoil (NASA TP-2969)


Airfoil sc20706-il
Details Dat file Parser  
(sc20706-il) NASA SC(2)-0706 AIRFOIL
NASA SC(2)-0706 airfoil (NASA TP-2969)
Max thickness 6% at 34% chord.
Max camber 1.6% at 82% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0706 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.004300
 0.005000  0.006500
 0.010000  0.008800
 0.020000  0.011700
 0.030000  0.013800
 0.040000  0.015500
 0.050000  0.016900
 0.060000  0.018100
 0.070000  0.019200
 0.080000  0.020200
 0.090000  0.021100
 0.100000  0.021900
 0.110000  0.022700
 0.120000  0.023400
 0.130000  0.024000
 0.140000  0.024600
 0.150000  0.025200
 0.160000  0.025700
 0.170000  0.026200
 0.180000  0.026600
 0.190000  0.027000
 0.200000  0.027400
 0.210000  0.027700
 0.220000  0.028000
 0.230000  0.028300
 0.240000  0.028600
 0.250000  0.028800
 0.260000  0.029000
 0.270000  0.029200
 0.280000  0.029400
 0.290000  0.029500
 0.300000  0.029600
 0.310000  0.029700
 0.320000  0.029800
 0.330000  0.029900
 0.340000  0.030000
 0.350000  0.030000
 0.360000  0.030000
 0.370000  0.030000
 0.380000  0.030000
 0.390000  0.030000
 0.400000  0.030000
 0.410000  0.029900
 0.420000  0.029800
 0.430000  0.029700
 0.440000  0.029600
 0.450000  0.029500
 0.460000  0.029400
 0.470000  0.029300
 0.480000  0.029100
 0.490000  0.028900
 0.500000  0.028700
 0.510000  0.028500
 0.520000  0.028300
 0.530000  0.028100
 0.540000  0.027800
 0.550000  0.027500
 0.560000  0.027200
 0.570000  0.026900
 0.580000  0.026600
 0.590000  0.026300
 0.600000  0.026000
 0.610000  0.025600
 0.620000  0.025200
 0.630000  0.024800
 0.640000  0.024400
 0.650000  0.024000
 0.660000  0.023600
 0.670000  0.023100
 0.680000  0.022600
 0.690000  0.022100
 0.700000  0.021600
 0.710000  0.021100
 0.720000  0.020600
 0.730000  0.020000
 0.740000  0.019400
 0.750000  0.018800
 0.760000  0.018200
 0.770000  0.017500
 0.780000  0.016800
 0.790000  0.016100
 0.800000  0.015400
 0.810000  0.014600
 0.820000  0.013800
 0.830000  0.012900
 0.840000  0.012000
 0.850000  0.011000
 0.860000  0.010000
 0.870000  0.008900
 0.880000  0.007700
 0.890000  0.006400
 0.900000  0.005100
 0.910000  0.003700
 0.920000  0.002200
 0.930000  0.000600
 0.940000 -0.001100
 0.950000 -0.002900
 0.960000 -0.004800
 0.970000 -0.006800
 0.980000 -0.008900
 0.990000 -0.011200
 1.000000 -0.013800

 0.000000  0.000000
 0.002000 -0.004300
 0.005000 -0.006500
 0.010000 -0.008800
 0.020000 -0.011700
 0.030000 -0.013800
 0.040000 -0.015500
 0.050000 -0.016900
 0.060000 -0.018100
 0.070000 -0.019200
 0.080000 -0.020200
 0.090000 -0.021100
 0.100000 -0.021900
 0.110000 -0.022700
 0.120000 -0.023400
 0.130000 -0.024000
 0.140000 -0.024600
 0.150000 -0.025100
 0.160000 -0.025600
 0.170000 -0.026100
 0.180000 -0.026500
 0.190000 -0.026900
 0.200000 -0.027300
 0.210000 -0.027700
 0.220000 -0.028000
 0.230000 -0.028300
 0.240000 -0.028600
 0.250000 -0.028800
 0.260000 -0.029000
 0.270000 -0.029200
 0.280000 -0.029400
 0.290000 -0.029600
 0.300000 -0.029700
 0.310000 -0.029800
 0.320000 -0.029900
 0.330000 -0.030000
 0.340000 -0.030000
 0.350000 -0.030000
 0.360000 -0.030000
 0.370000 -0.030000
 0.380000 -0.029900
 0.390000 -0.029800
 0.400000 -0.029700
 0.410000 -0.029600
 0.420000 -0.029400
 0.430000 -0.029200
 0.440000 -0.029000
 0.450000 -0.028700
 0.460000 -0.028400
 0.470000 -0.028100
 0.480000 -0.027800
 0.490000 -0.027400
 0.500000 -0.027000
 0.510000 -0.026600
 0.520000 -0.026100
 0.530000 -0.025600
 0.540000 -0.025100
 0.550000 -0.024600
 0.560000 -0.024000
 0.570000 -0.023400
 0.580000 -0.022800
 0.590000 -0.022200
 0.600000 -0.021600
 0.610000 -0.021000
 0.620000 -0.020400
 0.630000 -0.019700
 0.640000 -0.019000
 0.650000 -0.018300
 0.660000 -0.017600
 0.670000 -0.016900
 0.680000 -0.016200
 0.690000 -0.015500
 0.700000 -0.014800
 0.710000 -0.014100
 0.720000 -0.013400
 0.730000 -0.012700
 0.740000 -0.012000
 0.750000 -0.011300
 0.760000 -0.010600
 0.770000 -0.009900
 0.780000 -0.009300
 0.790000 -0.008700
 0.800000 -0.008100
 0.810000 -0.007500
 0.820000 -0.007000
 0.830000 -0.006500
 0.840000 -0.006100
 0.850000 -0.005700
 0.860000 -0.005400
 0.870000 -0.005200
 0.880000 -0.005100
 0.890000 -0.005100
 0.900000 -0.005200
 0.910000 -0.005400
 0.920000 -0.005800
 0.930000 -0.006400
 0.940000 -0.007200
 0.950000 -0.008200
 0.960000 -0.009500
 0.970000 -0.011100
 0.980000 -0.013000
 0.990000 -0.015200
 1.000000 -0.017700
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Polars for NASA SC(2)-0706 AIRFOIL (sc20706-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20706-il50,000924 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20706-il50,000525.3 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20706-il100,000938.2 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20706-il100,000533.3 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20706-il200,000940.6 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20706-il200,000544.1 at α=0.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20706-il500,000967 at α=0.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20706-il500,000555.8 at α=-0.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20706-il1,000,000996.6 at α=-0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20706-il1,000,000568 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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