NASA SC(2)-0010 AIRFOIL (sc20010-il)
NASA SC(2)-0010 AIRFOIL - NASA SC(2)-0010 airfoil (NASA TP-2969)
| Details | Dat file | Parser | |
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(sc20010-il) NASA SC(2)-0010 AIRFOIL NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA SC(2)-0010 AIRFOIL
103. 103.
0.000000 0.000000
0.002000 0.007600
0.005000 0.011600
0.010000 0.015500
0.020000 0.020700
0.030000 0.024300
0.040000 0.027000
0.050000 0.029200
0.060000 0.031100
0.070000 0.032800
0.080000 0.034300
0.090000 0.035700
0.100000 0.036900
0.110000 0.038000
0.120000 0.039000
0.130000 0.040000
0.140000 0.040900
0.150000 0.041700
0.160000 0.042500
0.170000 0.043200
0.180000 0.043900
0.190000 0.044500
0.200000 0.045100
0.210000 0.045600
0.220000 0.046100
0.230000 0.046600
0.240000 0.047000
0.250000 0.047400
0.260000 0.047800
0.270000 0.048100
0.280000 0.048400
0.290000 0.048700
0.300000 0.049000
0.310000 0.049200
0.320000 0.049400
0.330000 0.049600
0.340000 0.049700
0.350000 0.049800
0.360000 0.049900
0.370000 0.050000
0.380000 0.050000
0.390000 0.050000
0.400000 0.050000
0.410000 0.050000
0.420000 0.049900
0.430000 0.049800
0.440000 0.049700
0.450000 0.049600
0.460000 0.049400
0.470000 0.049200
0.480000 0.049000
0.490000 0.048700
0.500000 0.048400
0.510000 0.048100
0.520000 0.047800
0.530000 0.047400
0.540000 0.047000
0.550000 0.046500
0.560000 0.046000
0.570000 0.045500
0.580000 0.044900
0.590000 0.044300
0.600000 0.043600
0.610000 0.042800
0.620000 0.042000
0.630000 0.041100
0.640000 0.040200
0.650000 0.039200
0.660000 0.038200
0.670000 0.037150
0.680000 0.036100
0.690000 0.035050
0.700000 0.034000
0.710000 0.032950
0.720000 0.031900
0.730000 0.030850
0.740000 0.029800
0.750000 0.028750
0.760000 0.027700
0.770000 0.026650
0.780000 0.025600
0.790000 0.024550
0.800000 0.023500
0.810000 0.022450
0.820000 0.021400
0.830000 0.020350
0.840000 0.019300
0.850000 0.018250
0.860000 0.017200
0.870000 0.016150
0.880000 0.015100
0.890000 0.014050
0.900000 0.013000
0.910000 0.011950
0.920000 0.010900
0.930000 0.009850
0.940000 0.008800
0.950000 0.007750
0.960000 0.006700
0.970000 0.005650
0.980000 0.004600
0.990000 0.003550
1.000000 0.002500
0.000000 0.000000
0.002000 -0.007600
0.005000 -0.011600
0.010000 -0.015500
0.020000 -0.020700
0.030000 -0.024300
0.040000 -0.027000
0.050000 -0.029200
0.060000 -0.031100
0.070000 -0.032800
0.080000 -0.034300
0.090000 -0.035700
0.100000 -0.036900
0.110000 -0.038000
0.120000 -0.039000
0.130000 -0.040000
0.140000 -0.040900
0.150000 -0.041700
0.160000 -0.042500
0.170000 -0.043200
0.180000 -0.043900
0.190000 -0.044500
0.200000 -0.045100
0.210000 -0.045600
0.220000 -0.046100
0.230000 -0.046600
0.240000 -0.047000
0.250000 -0.047400
0.260000 -0.047800
0.270000 -0.048100
0.280000 -0.048400
0.290000 -0.048700
0.300000 -0.049000
0.310000 -0.049200
0.320000 -0.049400
0.330000 -0.049600
0.340000 -0.049700
0.350000 -0.049800
0.360000 -0.049900
0.370000 -0.050000
0.380000 -0.050000
0.390000 -0.050000
0.400000 -0.050000
0.410000 -0.050000
0.420000 -0.049900
0.430000 -0.049800
0.440000 -0.049700
0.450000 -0.049600
0.460000 -0.049400
0.470000 -0.049200
0.480000 -0.049000
0.490000 -0.048700
0.500000 -0.048400
0.510000 -0.048100
0.520000 -0.047800
0.530000 -0.047400
0.540000 -0.047000
0.550000 -0.046500
0.560000 -0.046000
0.570000 -0.045500
0.580000 -0.044900
0.590000 -0.044300
0.600000 -0.043600
0.610000 -0.042800
0.620000 -0.042000
0.630000 -0.041100
0.640000 -0.040200
0.650000 -0.039200
0.660000 -0.038200
0.670000 -0.037150
0.680000 -0.036100
0.690000 -0.035050
0.700000 -0.034000
0.710000 -0.032950
0.720000 -0.031900
0.730000 -0.030850
0.740000 -0.029800
0.750000 -0.028750
0.760000 -0.027700
0.770000 -0.026650
0.780000 -0.025600
0.790000 -0.024550
0.800000 -0.023500
0.810000 -0.022450
0.820000 -0.021400
0.830000 -0.020350
0.840000 -0.019300
0.850000 -0.018250
0.860000 -0.017200
0.870000 -0.016150
0.880000 -0.015100
0.890000 -0.014050
0.900000 -0.013000
0.910000 -0.011950
0.920000 -0.010900
0.930000 -0.009850
0.940000 -0.008800
0.950000 -0.007750
0.960000 -0.006700
0.970000 -0.005650
0.980000 -0.004600
0.990000 -0.003550
1.000000 -0.002500
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Polars for NASA SC(2)-0010 AIRFOIL (sc20010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20010-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 5 | 22.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 5 | 28.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 9 | 39.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 5 | 39 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 9 | 52 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 5 | 56.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 9 | 67.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 5 | 70.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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