Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

RAE 104 AIRFOIL (rae104-il)

RAE 104 AIRFOIL - RAE 104 airfoil


Airfoil rae104-il
Details Dat file Parser  
(rae104-il) RAE 104 AIRFOIL
RAE 104 airfoil
Max thickness 10% at 42% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RAE 104 AIRFOIL
       86.       86.

  0.000000  0.000000
  0.001000  0.003441
  0.002000  0.004863
  0.003000  0.005953
  0.004000  0.006870
  0.005000  0.007676
  0.006000  0.008404
  0.007000  0.009072
  0.007500  0.009387
  0.008000  0.009692
  0.009000  0.010274
  0.010000  0.010824
  0.012000  0.011842
  0.012500  0.012083
  0.014000  0.012776
  0.016000  0.013642
  0.018000  0.014452
  0.020000  0.015215
  0.025000  0.016960
  0.030000  0.018522
  0.035000  0.019950
  0.040000  0.021256
  0.050000  0.023617
  0.060000  0.025709
  0.070000  0.027592
  0.075000  0.028468
  0.080000  0.029307
  0.090000  0.030881
  0.100000  0.032336
  0.120000  0.034945
  0.140000  0.037222
  0.150000  0.038254
  0.160000  0.039224
  0.180000  0.040992
  0.200000  0.042556
  0.220000  0.043936
  0.240000  0.045149
  0.250000  0.045697
  0.260000  0.046208
  0.280000  0.047124
  0.300000  0.047905
  0.320000  0.048556
  0.340000  0.049082
  0.350000  0.049300
  0.360000  0.049488
  0.380000  0.049775
  0.400000  0.049946
  0.420000  0.050000
  0.440000  0.049937
  0.450000  0.049862
  0.460000  0.049756
  0.480000  0.049454
  0.500000  0.049027
  0.520000  0.048468
  0.540000  0.047769
  0.550000  0.047363
  0.560000  0.046917
  0.580000  0.045892
  0.600000  0.044650
  0.620000  0.043113
  0.640000  0.041370
  0.650000  0.040438
  0.660000  0.039473
  0.680000  0.037452
  0.700000  0.035331
  0.720000  0.033128
  0.740000  0.030861
  0.750000  0.029708
  0.760000  0.028545
  0.780000  0.026193
  0.800000  0.023819
  0.820000  0.021437
  0.840000  0.019055
  0.850000  0.017864
  0.860000  0.016673
  0.880000  0.014292
  0.900000  0.011910
  0.920000  0.009528
  0.925000  0.008932
  0.940000  0.007147
  0.950000  0.005955
  0.960000  0.004764
  0.975000  0.002977
  0.980000  0.002382
  0.987500  0.001489
  1.000000  0.000000

  0.000000  0.000000
  0.001000 -0.003441
  0.002000 -0.004863
  0.003000 -0.005953
  0.004000 -0.006870
  0.005000 -0.007676
  0.006000 -0.008404
  0.007000 -0.009072
  0.007500 -0.009387
  0.008000 -0.009692
  0.009000 -0.010274
  0.010000 -0.010824
  0.012000 -0.011842
  0.012500 -0.012083
  0.014000 -0.012776
  0.016000 -0.013642
  0.018000 -0.014452
  0.020000 -0.015215
  0.025000 -0.016960
  0.030000 -0.018522
  0.035000 -0.019950
  0.040000 -0.021256
  0.050000 -0.023617
  0.060000 -0.025709
  0.070000 -0.027592
  0.075000 -0.028468
  0.080000 -0.029307
  0.090000 -0.030881
  0.100000 -0.032336
  0.120000 -0.034945
  0.140000 -0.037222
  0.150000 -0.038254
  0.160000 -0.039224
  0.180000 -0.040992
  0.200000 -0.042556
  0.220000 -0.043936
  0.240000 -0.045149
  0.250000 -0.045697
  0.260000 -0.046208
  0.280000 -0.047124
  0.300000 -0.047905
  0.320000 -0.048556
  0.340000 -0.049082
  0.350000 -0.049300
  0.360000 -0.049488
  0.380000 -0.049775
  0.400000 -0.049946
  0.420000 -0.050000
  0.440000 -0.049937
  0.450000 -0.049862
  0.460000 -0.049756
  0.480000 -0.049454
  0.500000 -0.049027
  0.520000 -0.048468
  0.540000 -0.047769
  0.550000 -0.047363
  0.560000 -0.046917
  0.580000 -0.045892
  0.600000 -0.044650
  0.620000 -0.043113
  0.640000 -0.041370
  0.650000 -0.040438
  0.660000 -0.039473
  0.680000 -0.037452
  0.700000 -0.035331
  0.720000 -0.033128
  0.740000 -0.030861
  0.750000 -0.029708
  0.760000 -0.028545
  0.780000 -0.026193
  0.800000 -0.023819
  0.820000 -0.021437
  0.840000 -0.019055
  0.850000 -0.017864
  0.860000 -0.016673
  0.880000 -0.014292
  0.900000 -0.011910
  0.920000 -0.009528
  0.925000 -0.008932
  0.940000 -0.007147
  0.950000 -0.005955
  0.960000 -0.004764
  0.975000 -0.002977
  0.980000 -0.002382
  0.987500 -0.001489
  1.000000  0.000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

LWK 80-100PreviewDetails
NACA 0010-34PreviewDetails
NACA 0010-64PreviewDetails
NACA 64A-010 10.0%PreviewDetails
RAE 103 AIRFOILPreviewDetails
NASA SC(2)-0010 AIRFOILPreviewDetails
RAE 102 AIRFOILPreviewDetails
NACA 63A010 AIRFOILPreviewDetails
NACA/LANGLEY SYMMETRICALPreviewDetails
NACA 0010-35PreviewDetails

Polars for RAE 104 AIRFOIL (rae104-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae104-il50,000924.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae104-il50,000526.2 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   rae104-il100,000939.8 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae104-il100,000533.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   rae104-il200,000944.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae104-il200,000536.7 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae104-il500,000952.1 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae104-il500,000549.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae104-il1,000,000958.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae104-il1,000,000561.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit