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RAE 101 AIRFOIL (rae101-il)

RAE 101 AIRFOIL - RAE 101 airfoil


Airfoil rae101-il
Details Dat file Parser  
(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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Lednicer format dat file
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Polars for RAE 101 AIRFOIL (rae101-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae101-il50,000927.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae101-il50,000527.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae101-il100,000939 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae101-il100,000536.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae101-il200,000949.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae101-il200,000544.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae101-il500,000960.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae101-il500,000556.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae101-il1,000,000967.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae101-il1,000,000570.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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