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RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 104 AIRFOIL (rae104-il)
Reynolds number: 100,000
Max Cl/Cd: 33.38 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae104-il-100000-n5.txt
Download as CSV file: xf-rae104-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 104 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6448   0.09247   0.08733  -0.0247   1.0000   0.0225
 -11.000  -0.6556   0.08474   0.07961  -0.0297   1.0000   0.0222
 -10.750  -0.6727   0.07754   0.07236  -0.0346   1.0000   0.0220
 -10.500  -0.6914   0.07176   0.06651  -0.0377   1.0000   0.0218
 -10.250  -0.7104   0.06701   0.06166  -0.0390   1.0000   0.0217
 -10.000  -0.7293   0.06300   0.05752  -0.0387   1.0000   0.0216
  -9.750  -0.7468   0.05963   0.05400  -0.0367   1.0000   0.0215
  -9.500  -0.7635   0.05637   0.05055  -0.0336   1.0000   0.0215
  -9.250  -0.7746   0.05289   0.04681  -0.0307   1.0000   0.0215
  -9.000  -0.7821   0.04938   0.04297  -0.0277   1.0000   0.0217
  -8.750  -0.7852   0.04611   0.03930  -0.0246   1.0000   0.0221
  -8.500  -0.7844   0.04330   0.03600  -0.0214   1.0000   0.0227
  -8.250  -0.7813   0.04015   0.03262  -0.0190   1.0000   0.0238
  -8.000  -0.7722   0.03806   0.03033  -0.0168   1.0000   0.0248
  -7.750  -0.7617   0.03570   0.02767  -0.0145   1.0000   0.0254
  -7.500  -0.7490   0.03339   0.02502  -0.0122   1.0000   0.0261
  -7.250  -0.7340   0.03125   0.02258  -0.0102   1.0000   0.0270
  -7.000  -0.7169   0.02927   0.02030  -0.0084   1.0000   0.0283
  -6.750  -0.6986   0.02769   0.01842  -0.0066   1.0000   0.0302
  -6.500  -0.6801   0.02623   0.01672  -0.0050   1.0000   0.0327
  -6.250  -0.6631   0.02471   0.01519  -0.0033   1.0000   0.0349
  -6.000  -0.6465   0.02354   0.01396  -0.0014   1.0000   0.0371
  -5.750  -0.6310   0.02251   0.01284   0.0008   1.0000   0.0400
  -5.500  -0.6171   0.02163   0.01187   0.0032   1.0000   0.0444
  -5.250  -0.6052   0.02078   0.01103   0.0058   1.0000   0.0488
  -5.000  -0.5930   0.02004   0.01016   0.0085   1.0000   0.0538
  -4.750  -0.5814   0.01933   0.00946   0.0111   1.0000   0.0617
  -4.500  -0.5594   0.01854   0.00868   0.0117   0.9968   0.0757
  -4.250  -0.5307   0.01763   0.00790   0.0109   0.9907   0.1077
  -4.000  -0.5044   0.01648   0.00726   0.0102   0.9847   0.1960
  -3.750  -0.4861   0.01496   0.00670   0.0109   0.9776   0.3845
  -3.500  -0.4677   0.01402   0.00697   0.0131   0.9718   0.6265
  -3.250  -0.4417   0.01409   0.00712   0.0141   0.9658   0.7136
  -3.000  -0.4134   0.01427   0.00728   0.0147   0.9603   0.7595
  -2.750  -0.3813   0.01452   0.00743   0.0146   0.9565   0.7942
  -2.500  -0.3529   0.01478   0.00762   0.0154   0.9514   0.8207
  -2.250  -0.3226   0.01501   0.00775   0.0155   0.9469   0.8428
  -2.000  -0.2858   0.01524   0.00785   0.0142   0.9440   0.8583
  -1.750  -0.2495   0.01535   0.00785   0.0126   0.9409   0.8703
  -1.500  -0.2140   0.01547   0.00788   0.0111   0.9365   0.8775
  -1.250  -0.1810   0.01547   0.00780   0.0098   0.9320   0.8857
  -1.000  -0.1402   0.01552   0.00776   0.0071   0.9293   0.8905
  -0.750  -0.1086   0.01551   0.00769   0.0060   0.9244   0.8976
  -0.500  -0.0726   0.01554   0.00769   0.0041   0.9198   0.9021
  -0.250  -0.0342   0.01554   0.00766   0.0016   0.9162   0.9064
   0.000   0.0000   0.01551   0.00761   0.0000   0.9122   0.9121
   0.250   0.0342   0.01554   0.00766  -0.0016   0.9063   0.9162
   0.500   0.0726   0.01554   0.00769  -0.0041   0.9021   0.9198
   0.750   0.1085   0.01551   0.00769  -0.0060   0.8976   0.9244
   1.000   0.1402   0.01552   0.00776  -0.0071   0.8905   0.9293
   1.250   0.1809   0.01548   0.00780  -0.0098   0.8858   0.9320
   1.500   0.2140   0.01547   0.00788  -0.0111   0.8776   0.9365
   1.750   0.2495   0.01535   0.00785  -0.0126   0.8703   0.9409
   2.000   0.2857   0.01524   0.00788  -0.0142   0.8583   0.9440
   2.250   0.3226   0.01501   0.00775  -0.0155   0.8428   0.9469
   2.500   0.3529   0.01478   0.00762  -0.0153   0.8207   0.9514
   2.750   0.3812   0.01452   0.00743  -0.0147   0.7942   0.9565
   3.000   0.4134   0.01427   0.00728  -0.0147   0.7596   0.9603
   3.250   0.4416   0.01409   0.00712  -0.0141   0.7128   0.9659
   3.500   0.4677   0.01401   0.00696  -0.0131   0.6249   0.9718
   3.750   0.4862   0.01495   0.00670  -0.0109   0.3853   0.9776
   4.000   0.5045   0.01647   0.00726  -0.0102   0.1961   0.9847
   4.250   0.5307   0.01763   0.00790  -0.0109   0.1077   0.9907
   4.500   0.5594   0.01854   0.00868  -0.0117   0.0757   0.9968
   4.750   0.5814   0.01932   0.00946  -0.0111   0.0618   1.0000
   5.000   0.5930   0.02004   0.01016  -0.0085   0.0540   1.0000
   5.250   0.6052   0.02077   0.01103  -0.0058   0.0491   1.0000
   5.500   0.6172   0.02162   0.01186  -0.0032   0.0445   1.0000
   5.750   0.6310   0.02252   0.01284  -0.0008   0.0403   1.0000
   6.000   0.6465   0.02353   0.01396   0.0014   0.0372   1.0000
   6.250   0.6631   0.02471   0.01519   0.0033   0.0349   1.0000
   6.500   0.6801   0.02624   0.01673   0.0050   0.0327   1.0000
   6.750   0.6986   0.02769   0.01841   0.0066   0.0303   1.0000
   7.000   0.7169   0.02927   0.02031   0.0084   0.0282   1.0000
   7.250   0.7340   0.03127   0.02259   0.0102   0.0271   1.0000
   7.500   0.7491   0.03338   0.02501   0.0122   0.0261   1.0000
   7.750   0.7618   0.03569   0.02765   0.0145   0.0254   1.0000
   8.000   0.7723   0.03804   0.03032   0.0168   0.0248   1.0000
   8.250   0.7813   0.04009   0.03253   0.0189   0.0236   1.0000
   8.500   0.7846   0.04340   0.03607   0.0213   0.0228   1.0000
   8.750   0.7852   0.04610   0.03929   0.0246   0.0221   1.0000
   9.000   0.7817   0.04941   0.04301   0.0277   0.0216   1.0000
   9.250   0.7746   0.05289   0.04681   0.0307   0.0215   1.0000
   9.500   0.7643   0.05629   0.05046   0.0335   0.0215   1.0000
   9.750   0.7477   0.05957   0.05393   0.0366   0.0215   1.0000
  10.000   0.7301   0.06295   0.05746   0.0386   0.0216   1.0000
  10.250   0.7111   0.06697   0.06161   0.0390   0.0217   1.0000
  10.500   0.6921   0.07170   0.06645   0.0377   0.0218   1.0000
  10.750   0.6730   0.07756   0.07239   0.0345   0.0220   1.0000
  11.000   0.6569   0.08454   0.07941   0.0298   0.0222   1.0000
  11.250   0.6460   0.09223   0.08709   0.0248   0.0225   1.0000
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