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RAE 100 AIRFOIL (rae100-il)

RAE 100 AIRFOIL - RAE 100 airfoil


Airfoil rae100-il
Details Dat file Parser  
(rae100-il) RAE 100 AIRFOIL
RAE 100 airfoil
Max thickness 10% at 26% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAE 100 AIRFOIL
       86.       86.

  0.000000  0.000000
  0.001000  0.004680
  0.002000  0.006609
  0.003000  0.008083
  0.004000  0.009320
  0.005000  0.010406
  0.006000  0.011383
  0.007000  0.012278
  0.007500  0.012700
  0.008000  0.013107
  0.009000  0.013883
  0.010000  0.014613
  0.012000  0.015963
  0.012500  0.016281
  0.014000  0.017194
  0.016000  0.018329
  0.018000  0.019387
  0.020000  0.020377
  0.025000  0.022622
  0.030000  0.024605
  0.035000  0.026387
  0.040000  0.028006
  0.050000  0.030861
  0.060000  0.033316
  0.070000  0.035457
  0.075000  0.036429
  0.080000  0.037344
  0.090000  0.039016
  0.100000  0.040505
  0.120000  0.043019
  0.140000  0.045020
  0.150000  0.045859
  0.160000  0.046600
  0.180000  0.047823
  0.200000  0.048737
  0.220000  0.049382
  0.240000  0.049787
  0.250000  0.049908
  0.260000  0.049978
  0.280000  0.049976
  0.300000  0.049799
  0.320000  0.049464
  0.340000  0.048983
  0.350000  0.048691
  0.360000  0.048369
  0.380000  0.047633
  0.400000  0.046785
  0.420000  0.045834
  0.440000  0.044789
  0.450000  0.044234
  0.460000  0.043657
  0.480000  0.042447
  0.500000  0.041163
  0.520000  0.039814
  0.540000  0.038405
  0.550000  0.037680
  0.560000  0.036943
  0.580000  0.035432
  0.600000  0.033879
  0.620000  0.032288
  0.640000  0.030665
  0.650000  0.029843
  0.660000  0.029015
  0.680000  0.027343
  0.700000  0.025654
  0.720000  0.023953
  0.740000  0.022245
  0.750000  0.021389
  0.760000  0.020533
  0.780000  0.018822
  0.800000  0.017111
  0.820000  0.015400
  0.840000  0.013689
  0.850000  0.012833
  0.860000  0.011978
  0.880000  0.010267
  0.900000  0.008556
  0.920000  0.006844
  0.925000  0.006427
  0.940000  0.005133
  0.950000  0.004278
  0.960000  0.003422
  0.975000  0.002139
  0.980000  0.001711
  0.987500  0.001069
  1.000000  0.000000

  0.000000  0.000000
  0.001000 -0.004680
  0.002000 -0.006609
  0.003000 -0.008083
  0.004000 -0.009320
  0.005000 -0.010406
  0.006000 -0.011383
  0.007000 -0.012278
  0.007500 -0.012700
  0.008000 -0.013107
  0.009000 -0.013883
  0.010000 -0.014613
  0.012000 -0.015963
  0.012500 -0.016281
  0.014000 -0.017194
  0.016000 -0.018329
  0.018000 -0.019387
  0.020000 -0.020377
  0.025000 -0.022622
  0.030000 -0.024605
  0.035000 -0.026387
  0.040000 -0.028006
  0.050000 -0.030861
  0.060000 -0.033316
  0.070000 -0.035457
  0.075000 -0.036429
  0.080000 -0.037344
  0.090000 -0.039016
  0.100000 -0.040505
  0.120000 -0.043019
  0.140000 -0.045020
  0.150000 -0.045859
  0.160000 -0.046600
  0.180000 -0.047823
  0.200000 -0.048737
  0.220000 -0.049382
  0.240000 -0.049787
  0.250000 -0.049908
  0.260000 -0.049978
  0.280000 -0.049976
  0.300000 -0.049799
  0.320000 -0.049464
  0.340000 -0.048983
  0.350000 -0.048691
  0.360000 -0.048369
  0.380000 -0.047633
  0.400000 -0.046785
  0.420000 -0.045834
  0.440000 -0.044789
  0.450000 -0.044234
  0.460000 -0.043657
  0.480000 -0.042447
  0.500000 -0.041163
  0.520000 -0.039814
  0.540000 -0.038405
  0.550000 -0.037680
  0.560000 -0.036943
  0.580000 -0.035432
  0.600000 -0.033879
  0.620000 -0.032288
  0.640000 -0.030665
  0.650000 -0.029843
  0.660000 -0.029015
  0.680000 -0.027343
  0.700000 -0.025654
  0.720000 -0.023953
  0.740000 -0.022245
  0.750000 -0.021389
  0.760000 -0.020533
  0.780000 -0.018822
  0.800000 -0.017111
  0.820000 -0.015400
  0.840000 -0.013689
  0.850000 -0.012833
  0.860000 -0.011978
  0.880000 -0.010267
  0.900000 -0.008556
  0.920000 -0.006844
  0.925000 -0.006427
  0.940000 -0.005133
  0.950000 -0.004278
  0.960000 -0.003422
  0.975000 -0.002139
  0.980000 -0.001711
  0.987500 -0.001069
  1.000000  0.000000
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Polars for RAE 100 AIRFOIL (rae100-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae100-il50,000924.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae100-il50,000526.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae100-il100,000935.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae100-il100,000535.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae100-il200,000946.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae100-il200,000545 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   rae100-il500,000960.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae100-il500,000560.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rae100-il1,000,000974.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae100-il1,000,000574.8 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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