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RAE 102 AIRFOIL (rae102-il)

RAE 102 AIRFOIL - RAE 102 airfoil


Airfoil rae102-il
Details Dat file Parser  
(rae102-il) RAE 102 AIRFOIL
RAE 102 airfoil
Max thickness 10% at 36% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAE 102 AIRFOIL
       86.       86.

  0.000000  0.000000
  0.001000  0.003701
  0.002000  0.005231
  0.003000  0.006402
  0.004000  0.007388
  0.005000  0.008254
  0.006000  0.009036
  0.007000  0.009753
  0.007500  0.010092
  0.008000  0.010420
  0.009000  0.011044
  0.010000  0.011634
  0.012000  0.012727
  0.012500  0.012985
  0.014000  0.013727
  0.016000  0.014655
  0.018000  0.015523
  0.020000  0.016340
  0.025000  0.018205
  0.030000  0.019873
  0.035000  0.021390
  0.040000  0.022786
  0.050000  0.025293
  0.060000  0.027506
  0.070000  0.029491
  0.075000  0.030412
  0.080000  0.031291
  0.090000  0.032937
  0.100000  0.034450
  0.120000  0.037142
  0.140000  0.039463
  0.150000  0.040505
  0.160000  0.041475
  0.180000  0.043219
  0.200000  0.044727
  0.220000  0.046021
  0.240000  0.047117
  0.250000  0.047595
  0.260000  0.048027
  0.280000  0.048761
  0.300000  0.049323
  0.320000  0.049718
  0.340000  0.049943
  0.350000  0.049992
  0.360000  0.049997
  0.380000  0.049869
  0.400000  0.049534
  0.420000  0.048942
  0.440000  0.048154
  0.450000  0.047699
  0.460000  0.047207
  0.480000  0.046124
  0.500000  0.044920
  0.520000  0.043608
  0.540000  0.042201
  0.550000  0.041465
  0.560000  0.040709
  0.580000  0.039142
  0.600000  0.037507
  0.620000  0.035813
  0.640000  0.034068
  0.650000  0.033179
  0.660000  0.032279
  0.680000  0.030454
  0.700000  0.028598
  0.720000  0.026720
  0.740000  0.024825
  0.750000  0.023873
  0.760000  0.022920
  0.780000  0.021011
  0.800000  0.019101
  0.820000  0.017191
  0.840000  0.015281
  0.850000  0.014326
  0.860000  0.013371
  0.880000  0.011461
  0.900000  0.009551
  0.920000  0.007641
  0.925000  0.007163
  0.940000  0.005730
  0.950000  0.004775
  0.960000  0.003820
  0.975000  0.002388
  0.980000  0.001910
  0.987500  0.001194
  1.000000  0.000000

  0.000000  0.000000
  0.001000 -0.003701
  0.002000 -0.005231
  0.003000 -0.006402
  0.004000 -0.007388
  0.005000 -0.008254
  0.006000 -0.009036
  0.007000 -0.009753
  0.007500 -0.010092
  0.008000 -0.010420
  0.009000 -0.011044
  0.010000 -0.011634
  0.012000 -0.012727
  0.012500 -0.012985
  0.014000 -0.013727
  0.016000 -0.014655
  0.018000 -0.015523
  0.020000 -0.016340
  0.025000 -0.018205
  0.030000 -0.019873
  0.035000 -0.021390
  0.040000 -0.022786
  0.050000 -0.025293
  0.060000 -0.027506
  0.070000 -0.029491
  0.075000 -0.030412
  0.080000 -0.031291
  0.090000 -0.032937
  0.100000 -0.034450
  0.120000 -0.037142
  0.140000 -0.039463
  0.150000 -0.040505
  0.160000 -0.041475
  0.180000 -0.043219
  0.200000 -0.044727
  0.220000 -0.046021
  0.240000 -0.047117
  0.250000 -0.047595
  0.260000 -0.048027
  0.280000 -0.048761
  0.300000 -0.049323
  0.320000 -0.049718
  0.340000 -0.049943
  0.350000 -0.049992
  0.360000 -0.049997
  0.380000 -0.049869
  0.400000 -0.049534
  0.420000 -0.048942
  0.440000 -0.048154
  0.450000 -0.047699
  0.460000 -0.047207
  0.480000 -0.046124
  0.500000 -0.044920
  0.520000 -0.043608
  0.540000 -0.042201
  0.550000 -0.041465
  0.560000 -0.040709
  0.580000 -0.039142
  0.600000 -0.037507
  0.620000 -0.035813
  0.640000 -0.034068
  0.650000 -0.033179
  0.660000 -0.032279
  0.680000 -0.030454
  0.700000 -0.028598
  0.720000 -0.026720
  0.740000 -0.024825
  0.750000 -0.023873
  0.760000 -0.022920
  0.780000 -0.021011
  0.800000 -0.019101
  0.820000 -0.017191
  0.840000 -0.015281
  0.850000 -0.014326
  0.860000 -0.013371
  0.880000 -0.011461
  0.900000 -0.009551
  0.920000 -0.007641
  0.925000 -0.007163
  0.940000 -0.005730
  0.950000 -0.004775
  0.960000 -0.003820
  0.975000 -0.002388
  0.980000 -0.001910
  0.987500 -0.001194
  1.000000  0.000000
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Polars for RAE 102 AIRFOIL (rae102-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae102-il50,000928.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae102-il50,000527.4 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rae102-il100,000939.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae102-il100,000536.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   rae102-il200,000950.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   rae102-il200,000541.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rae102-il500,000957.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae102-il500,000554.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rae102-il1,000,000965.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae102-il1,000,000568.3 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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