RAE 101 AIRFOIL (rae101-il)
RAE 101 AIRFOIL - RAE 101 airfoil
| Details | Dat file | Parser | |
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(rae101-il) RAE 101 AIRFOIL RAE 101 airfoil Max thickness 10% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAE 101 AIRFOIL
86. 86.
0.000000 0.000000
0.001000 0.003905
0.002000 0.005518
0.003000 0.006753
0.004000 0.007792
0.005000 0.008705
0.006000 0.009529
0.007000 0.010285
0.007500 0.010642
0.008000 0.010987
0.009000 0.011644
0.010000 0.012265
0.012000 0.013416
0.012500 0.013687
0.014000 0.014469
0.016000 0.015445
0.018000 0.016357
0.020000 0.017215
0.025000 0.019174
0.030000 0.020924
0.035000 0.022513
0.040000 0.023974
0.050000 0.026593
0.060000 0.028898
0.070000 0.030959
0.075000 0.031913
0.080000 0.032822
0.090000 0.034519
0.100000 0.036073
0.120000 0.038820
0.140000 0.041162
0.150000 0.042202
0.160000 0.043163
0.180000 0.044867
0.200000 0.046304
0.220000 0.047496
0.240000 0.048455
0.250000 0.048851
0.260000 0.049190
0.280000 0.049700
0.300000 0.049969
0.320000 0.049956
0.340000 0.049724
0.350000 0.049536
0.360000 0.049307
0.380000 0.048728
0.400000 0.048005
0.420000 0.047153
0.440000 0.046183
0.450000 0.045657
0.460000 0.045106
0.480000 0.043932
0.500000 0.042670
0.520000 0.041329
0.540000 0.039915
0.550000 0.039183
0.560000 0.038436
0.580000 0.036899
0.600000 0.035310
0.620000 0.033676
0.640000 0.032003
0.650000 0.031154
0.660000 0.030297
0.680000 0.028563
0.700000 0.026807
0.720000 0.025034
0.740000 0.023251
0.750000 0.022357
0.760000 0.021463
0.780000 0.019674
0.800000 0.017886
0.820000 0.016097
0.840000 0.014309
0.850000 0.013414
0.860000 0.012520
0.880000 0.010731
0.900000 0.008943
0.920000 0.007154
0.925000 0.006707
0.940000 0.005366
0.950000 0.004471
0.960000 0.003577
0.975000 0.002236
0.980000 0.001789
0.987500 0.001118
1.000000 0.000000
0.000000 0.000000
0.001000 -0.003905
0.002000 -0.005518
0.003000 -0.006753
0.004000 -0.007792
0.005000 -0.008705
0.006000 -0.009529
0.007000 -0.010285
0.007500 -0.010642
0.008000 -0.010987
0.009000 -0.011644
0.010000 -0.012265
0.012000 -0.013416
0.012500 -0.013687
0.014000 -0.014469
0.016000 -0.015445
0.018000 -0.016357
0.020000 -0.017215
0.025000 -0.019174
0.030000 -0.020924
0.035000 -0.022513
0.040000 -0.023974
0.050000 -0.026593
0.060000 -0.028898
0.070000 -0.030959
0.075000 -0.031913
0.080000 -0.032822
0.090000 -0.034519
0.100000 -0.036073
0.120000 -0.038820
0.140000 -0.041162
0.150000 -0.042202
0.160000 -0.043163
0.180000 -0.044867
0.200000 -0.046304
0.220000 -0.047496
0.240000 -0.048455
0.250000 -0.048851
0.260000 -0.049190
0.280000 -0.049700
0.300000 -0.049969
0.320000 -0.049956
0.340000 -0.049724
0.350000 -0.049536
0.360000 -0.049307
0.380000 -0.048728
0.400000 -0.048005
0.420000 -0.047153
0.440000 -0.046183
0.450000 -0.045657
0.460000 -0.045106
0.480000 -0.043932
0.500000 -0.042670
0.520000 -0.041329
0.540000 -0.039915
0.550000 -0.039183
0.560000 -0.038436
0.580000 -0.036899
0.600000 -0.035310
0.620000 -0.033676
0.640000 -0.032003
0.650000 -0.031154
0.660000 -0.030297
0.680000 -0.028563
0.700000 -0.026807
0.720000 -0.025034
0.740000 -0.023251
0.750000 -0.022357
0.760000 -0.021463
0.780000 -0.019674
0.800000 -0.017886
0.820000 -0.016097
0.840000 -0.014309
0.850000 -0.013414
0.860000 -0.012520
0.880000 -0.010731
0.900000 -0.008943
0.920000 -0.007154
0.925000 -0.006707
0.940000 -0.005366
0.950000 -0.004471
0.960000 -0.003577
0.975000 -0.002236
0.980000 -0.001789
0.987500 -0.001118
1.000000 0.000000
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Polars for RAE 101 AIRFOIL (rae101-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae101-il | 50,000 | 9 | 27.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 50,000 | 5 | 27.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 100,000 | 9 | 39 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 100,000 | 5 | 36.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 200,000 | 9 | 49.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 200,000 | 5 | 44.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 500,000 | 9 | 60.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 500,000 | 5 | 56.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 1,000,000 | 9 | 67.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 1,000,000 | 5 | 70.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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