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NASA SC(2)-0612 AIRFOIL (sc20612-il)

NASA SC(2)-0612 AIRFOIL - NASA SC(2)-0612 airfoil (NASA TP-2969)


Airfoil sc20612-il
Details Dat file Parser  
(sc20612-il) NASA SC(2)-0612 AIRFOIL
NASA SC(2)-0612 airfoil (NASA TP-2969)
Max thickness 12% at 37% chord.
Max camber 1.9% at 81% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NASA SC(2)-0612 AIRFOIL
      103.      103.

 0.000000  0.000000
 0.002000  0.009200
 0.005000  0.014100
 0.010000  0.019000
 0.020000  0.025200
 0.030000  0.029600
 0.040000  0.032900
 0.050000  0.035500
 0.060000  0.037800
 0.070000  0.039800
 0.080000  0.041600
 0.090000  0.043200
 0.100000  0.044700
 0.110000  0.046000
 0.120000  0.047200
 0.130000  0.048400
 0.140000  0.049500
 0.150000  0.050500
 0.160000  0.051400
 0.170000  0.052300
 0.180000  0.053100
 0.190000  0.053800
 0.200000  0.054500
 0.210000  0.055100
 0.220000  0.055700
 0.230000  0.056300
 0.240000  0.056800
 0.250000  0.057300
 0.260000  0.057700
 0.270000  0.058100
 0.280000  0.058500
 0.290000  0.058800
 0.300000  0.059100
 0.310000  0.059300
 0.320000  0.059500
 0.330000  0.059700
 0.340000  0.059900
 0.350000  0.060000
 0.360000  0.060100
 0.370000  0.060200
 0.380000  0.060200
 0.390000  0.060200
 0.400000  0.060200
 0.410000  0.060200
 0.420000  0.060100
 0.430000  0.060000
 0.440000  0.059900
 0.450000  0.059800
 0.460000  0.059600
 0.470000  0.059400
 0.480000  0.059200
 0.490000  0.058900
 0.500000  0.058600
 0.510000  0.058300
 0.520000  0.058000
 0.530000  0.057600
 0.540000  0.057200
 0.550000  0.056800
 0.560000  0.056300
 0.570000  0.055800
 0.580000  0.055300
 0.590000  0.054700
 0.600000  0.054100
 0.610000  0.053400
 0.620000  0.052700
 0.630000  0.052000
 0.640000  0.051200
 0.650000  0.050400
 0.660000  0.049500
 0.670000  0.048600
 0.680000  0.047600
 0.690000  0.046600
 0.700000  0.045600
 0.710000  0.044500
 0.720000  0.043400
 0.730000  0.042200
 0.740000  0.041000
 0.750000  0.039700
 0.760000  0.038400
 0.770000  0.037100
 0.780000  0.035700
 0.790000  0.034300
 0.800000  0.032800
 0.810000  0.031300
 0.820000  0.029700
 0.830000  0.028100
 0.840000  0.026500
 0.850000  0.024800
 0.860000  0.023100
 0.870000  0.021300
 0.880000  0.019500
 0.890000  0.017600
 0.900000  0.015700
 0.910000  0.013700
 0.920000  0.011700
 0.930000  0.009600
 0.940000  0.007500
 0.950000  0.005300
 0.960000  0.003100
 0.970000  0.000800
 0.980000 -0.001600
 0.990000 -0.004100
 1.000000 -0.006700

 0.000000  0.000000
 0.002000 -0.009200
 0.005000 -0.014100
 0.010000 -0.019000
 0.020000 -0.025200
 0.030000 -0.029600
 0.040000 -0.032900
 0.050000 -0.035500
 0.060000 -0.037800
 0.070000 -0.039800
 0.080000 -0.041600
 0.090000 -0.043200
 0.100000 -0.044700
 0.110000 -0.046000
 0.120000 -0.047300
 0.130000 -0.048500
 0.140000 -0.049600
 0.150000 -0.050600
 0.160000 -0.051500
 0.170000 -0.052400
 0.180000 -0.053200
 0.190000 -0.054000
 0.200000 -0.054700
 0.210000 -0.055400
 0.220000 -0.056000
 0.230000 -0.056500
 0.240000 -0.057000
 0.250000 -0.057500
 0.260000 -0.057900
 0.270000 -0.058300
 0.280000 -0.058600
 0.290000 -0.058900
 0.300000 -0.059200
 0.310000 -0.059400
 0.320000 -0.059500
 0.330000 -0.059600
 0.340000 -0.059700
 0.350000 -0.059800
 0.360000 -0.059800
 0.370000 -0.059800
 0.380000 -0.059800
 0.390000 -0.059700
 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 -0.056700
 0.490000 -0.056100
 0.500000 -0.055400
 0.510000 -0.054600
 0.520000 -0.053800
 0.530000 -0.052900
 0.540000 -0.051900
 0.550000 -0.050900
 0.560000 -0.049700
 0.570000 -0.048500
 0.580000 -0.047200
 0.590000 -0.045800
 0.600000 -0.044400
 0.610000 -0.042900
 0.620000 -0.041400
 0.630000 -0.039800
 0.640000 -0.038200
 0.650000 -0.036500
 0.660000 -0.034800
 0.670000 -0.033000
 0.680000 -0.031200
 0.690000 -0.029400
 0.700000 -0.027600
 0.710000 -0.025800
 0.720000 -0.024000
 0.730000 -0.022200
 0.740000 -0.020400
 0.750000 -0.018600
 0.760000 -0.016800
 0.770000 -0.015000
 0.780000 -0.013300
 0.790000 -0.011700
 0.800000 -0.010200
 0.810000 -0.008700
 0.820000 -0.007300
 0.830000 -0.006000
 0.840000 -0.004800
 0.850000 -0.003700
 0.860000 -0.002800
 0.870000 -0.002100
 0.880000 -0.001600
 0.890000 -0.001200
 0.900000 -0.001000
 0.910000 -0.001000
 0.920000 -0.001300
 0.930000 -0.001800
 0.940000 -0.002500
 0.950000 -0.003500
 0.960000 -0.004800
 0.970000 -0.006300
 0.980000 -0.008100
 0.990000 -0.010200
 1.000000 -0.012500
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Polars for NASA SC(2)-0612 AIRFOIL (sc20612-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sc20612-il50,000924.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20612-il50,000523.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20612-il100,000929.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20612-il100,000531.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20612-il200,000940.5 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20612-il200,000544.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20612-il500,000963.6 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20612-il500,000565 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sc20612-il1,000,000977.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   sc20612-il1,000,000579.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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