NASA SC(2)-0612 AIRFOIL (sc20612-il)
NASA SC(2)-0612 AIRFOIL - NASA SC(2)-0612 airfoil (NASA TP-2969)
| 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
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NASA SC(2)-0612 AIRFOIL (sc20612-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20612-il | 50,000 | 9 | 24.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 50,000 | 5 | 23.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 100,000 | 9 | 29.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 100,000 | 5 | 31.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 200,000 | 9 | 40.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 200,000 | 5 | 44.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 500,000 | 9 | 63.6 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 500,000 | 5 | 65 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20612-il | 1,000,000 | 9 | 77.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20612-il | 1,000,000 | 5 | 79.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||