NASA SC(2)-0712 AIRFOIL (sc20712-il)
NASA SC(2)-0712 AIRFOIL - NASA SC(2)-0712 airfoil (NASA TP-2969)
| Details | Dat file | Parser | |
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(sc20712-il) NASA SC(2)-0712 AIRFOIL NASA SC(2)-0712 airfoil (NASA TP-2969) Max thickness 12% at 37% chord. Max camber 2.2% at 81% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA SC(2)-0712 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 0.029400
0.040000 0.032700
0.050000 0.035400
0.060000 0.037700
0.070000 0.039700
0.080000 0.041500
0.090000 0.043100
0.100000 0.044600
0.110000 0.045900
0.120000 0.047100
0.130000 0.048300
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 0.055100
0.220000 0.055700
0.230000 0.056200
0.240000 0.056700
0.250000 0.057200
0.260000 0.057600
0.270000 0.058000
0.280000 0.058400
0.290000 0.058700
0.300000 0.059000
0.310000 0.059200
0.320000 0.059400
0.330000 0.059600
0.340000 0.059800
0.350000 0.059900
0.360000 0.060000
0.370000 0.060100
0.380000 0.060100
0.390000 0.060100
0.400000 0.060100
0.410000 0.060100
0.420000 0.060000
0.430000 0.059900
0.440000 0.059800
0.450000 0.059600
0.460000 0.059400
0.470000 0.059200
0.480000 0.059000
0.490000 0.058700
0.500000 0.058400
0.510000 0.058100
0.520000 0.057700
0.530000 0.057300
0.540000 0.056900
0.550000 0.056400
0.560000 0.055900
0.570000 0.055400
0.580000 0.054900
0.590000 0.054300
0.600000 0.053700
0.610000 0.053000
0.620000 0.052300
0.630000 0.051600
0.640000 0.050800
0.650000 0.050000
0.660000 0.049100
0.670000 0.048200
0.680000 0.047200
0.690000 0.046200
0.700000 0.045100
0.710000 0.044000
0.720000 0.042800
0.730000 0.041600
0.740000 0.040300
0.750000 0.039000
0.760000 0.037600
0.770000 0.036200
0.780000 0.034700
0.790000 0.033200
0.800000 0.031600
0.810000 0.030000
0.820000 0.028300
0.830000 0.026600
0.840000 0.024800
0.850000 0.023000
0.860000 0.021100
0.870000 0.019200
0.880000 0.017200
0.890000 0.015200
0.900000 0.013100
0.910000 0.011000
0.920000 0.008800
0.930000 0.006500
0.940000 0.004200
0.950000 0.001800
0.960000 -0.000700
0.970000 -0.003300
0.980000 -0.006000
0.990000 -0.008800
1.000000 -0.011700
0.000000 0.000000
0.002000 -0.009200
0.005000 -0.014100
0.010000 -0.019000
0.020000 -0.025200
0.030000 -0.029400
0.040000 -0.032700
0.050000 -0.035300
0.060000 -0.037600
0.070000 -0.039600
0.080000 -0.041400
0.090000 -0.043000
0.100000 -0.044500
0.110000 -0.045900
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 -0.053900
0.200000 -0.054600
0.210000 -0.055300
0.220000 -0.055900
0.230000 -0.056400
0.240000 -0.056900
0.250000 -0.057400
0.260000 -0.057800
0.270000 -0.058200
0.280000 -0.058500
0.290000 -0.058800
0.300000 -0.059100
0.310000 -0.059300
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 -0.053700
0.530000 -0.052800
0.540000 -0.051800
0.550000 -0.050800
0.560000 -0.049600
0.570000 -0.048400
0.580000 -0.047100
0.590000 -0.045700
0.600000 -0.044300
0.610000 -0.042900
0.620000 -0.041400
0.630000 -0.039800
0.640000 -0.038200
0.650000 -0.036600
0.660000 -0.034900
0.670000 -0.033200
0.680000 -0.031500
0.690000 -0.029800
0.700000 -0.028000
0.710000 -0.026200
0.720000 -0.024400
0.730000 -0.022600
0.740000 -0.020800
0.750000 -0.019100
0.760000 -0.017400
0.770000 -0.015700
0.780000 -0.014100
0.790000 -0.012500
0.800000 -0.011000
0.810000 -0.009500
0.820000 -0.008200
0.830000 -0.007000
0.840000 -0.005900
0.850000 -0.005000
0.860000 -0.004300
0.870000 -0.003800
0.880000 -0.003500
0.890000 -0.003300
0.900000 -0.003400
0.910000 -0.003600
0.920000 -0.004100
0.930000 -0.004900
0.940000 -0.005900
0.950000 -0.007200
0.960000 -0.008700
0.970000 -0.010500
0.980000 -0.012600
0.990000 -0.015000
1.000000 -0.017700
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Polars for NASA SC(2)-0712 AIRFOIL (sc20712-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20712-il | 50,000 | 9 | 24.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 50,000 | 5 | 23.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 100,000 | 9 | 32 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 100,000 | 5 | 33.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 200,000 | 9 | 43.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 200,000 | 5 | 47.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 500,000 | 9 | 70.6 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 500,000 | 5 | 64.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 1,000,000 | 9 | 85.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 1,000,000 | 5 | 80.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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