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RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAE 101 AIRFOIL (rae101-il)
Reynolds number: 50,000
Max Cl/Cd: 27.44 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae101-il-50000-n5.txt
Download as CSV file: xf-rae101-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 101 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7123   0.09231   0.08506  -0.0126   1.0000   0.0471
 -10.750  -0.7287   0.08522   0.07795  -0.0175   1.0000   0.0468
 -10.500  -0.7464   0.07896   0.07165  -0.0216   1.0000   0.0465
 -10.250  -0.7651   0.07363   0.06623  -0.0244   1.0000   0.0462
 -10.000  -0.7844   0.06915   0.06163  -0.0253   1.0000   0.0460
  -9.750  -0.8015   0.06523   0.05753  -0.0247   1.0000   0.0460
  -9.500  -0.8139   0.06119   0.05320  -0.0239   1.0000   0.0463
  -9.250  -0.8221   0.05723   0.04885  -0.0227   1.0000   0.0469
  -9.000  -0.8258   0.05353   0.04461  -0.0212   1.0000   0.0478
  -8.750  -0.8176   0.05024   0.04124  -0.0204   1.0000   0.0494
  -8.500  -0.8076   0.04733   0.03808  -0.0193   1.0000   0.0510
  -8.250  -0.7954   0.04432   0.03474  -0.0181   1.0000   0.0523
  -8.000  -0.7807   0.04143   0.03148  -0.0169   1.0000   0.0541
  -7.750  -0.7641   0.03891   0.02849  -0.0156   1.0000   0.0577
  -7.500  -0.7451   0.03652   0.02582  -0.0146   1.0000   0.0614
  -7.250  -0.7239   0.03450   0.02365  -0.0137   1.0000   0.0651
  -7.000  -0.7012   0.03260   0.02147  -0.0127   1.0000   0.0703
  -6.750  -0.6802   0.03094   0.01978  -0.0117   1.0000   0.0770
  -6.500  -0.6581   0.02941   0.01804  -0.0105   1.0000   0.0846
  -6.250  -0.6390   0.02795   0.01662  -0.0092   1.0000   0.0946
  -6.000  -0.6203   0.02655   0.01518  -0.0078   1.0000   0.1077
  -5.750  -0.6022   0.02517   0.01379  -0.0064   1.0000   0.1263
  -5.500  -0.5858   0.02365   0.01248  -0.0050   1.0000   0.1556
  -5.250  -0.5708   0.02194   0.01123  -0.0035   1.0000   0.2129
  -5.000  -0.5582   0.02044   0.01053  -0.0015   1.0000   0.3270
  -4.750  -0.5428   0.01978   0.01023   0.0010   1.0000   0.4287
  -4.500  -0.5258   0.01943   0.00999   0.0035   1.0000   0.4954
  -4.250  -0.5082   0.01920   0.00983   0.0060   1.0000   0.5475
  -4.000  -0.4901   0.01903   0.00970   0.0086   1.0000   0.5912
  -3.750  -0.4715   0.01888   0.00955   0.0111   1.0000   0.6291
  -3.500  -0.4523   0.01872   0.00935   0.0135   1.0000   0.6624
  -3.250  -0.4323   0.01855   0.00916   0.0157   1.0000   0.6917
  -3.000  -0.4115   0.01837   0.00894   0.0176   1.0000   0.7180
  -2.750  -0.3897   0.01818   0.00873   0.0193   1.0000   0.7418
  -2.500  -0.3682   0.01797   0.00845   0.0208   1.0000   0.7654
  -2.250  -0.3445   0.01781   0.00825   0.0219   1.0000   0.7873
  -2.000  -0.3207   0.01764   0.00804   0.0229   1.0000   0.8103
  -1.750  -0.2938   0.01753   0.00790   0.0232   1.0000   0.8327
  -1.500  -0.2644   0.01745   0.00776   0.0229   1.0000   0.8561
  -1.250  -0.2315   0.01742   0.00769   0.0218   1.0000   0.8805
  -1.000  -0.1919   0.01744   0.00767   0.0192   1.0000   0.9035
  -0.750  -0.1507   0.01747   0.00764   0.0161   1.0000   0.9276
  -0.500  -0.1036   0.01751   0.00763   0.0116   1.0000   0.9494
  -0.250  -0.0564   0.01753   0.00763   0.0068   1.0000   0.9721
   0.000   0.0000   0.01751   0.00761   0.0000   0.9901   0.9901
   0.250   0.0564   0.01753   0.00763  -0.0068   0.9721   1.0000
   0.500   0.1035   0.01751   0.00763  -0.0116   0.9495   1.0000
   0.750   0.1505   0.01747   0.00764  -0.0161   0.9277   1.0000
   1.000   0.1917   0.01744   0.00767  -0.0192   0.9036   1.0000
   1.250   0.2314   0.01742   0.00769  -0.0218   0.8805   1.0000
   1.500   0.2643   0.01745   0.00776  -0.0229   0.8562   1.0000
   1.750   0.2937   0.01753   0.00790  -0.0232   0.8327   1.0000
   2.000   0.3206   0.01764   0.00804  -0.0229   0.8103   1.0000
   2.250   0.3444   0.01780   0.00824  -0.0219   0.7874   1.0000
   2.500   0.3681   0.01797   0.00844  -0.0208   0.7655   1.0000
   2.750   0.3897   0.01818   0.00873  -0.0193   0.7418   1.0000
   3.000   0.4115   0.01837   0.00894  -0.0176   0.7181   1.0000
   3.250   0.4322   0.01855   0.00916  -0.0157   0.6917   1.0000
   3.500   0.4522   0.01872   0.00935  -0.0135   0.6624   1.0000
   3.750   0.4714   0.01888   0.00955  -0.0111   0.6292   1.0000
   4.000   0.4900   0.01903   0.00969  -0.0086   0.5912   1.0000
   4.250   0.5081   0.01920   0.00983  -0.0060   0.5475   1.0000
   4.500   0.5257   0.01943   0.00999  -0.0034   0.4955   1.0000
   4.750   0.5427   0.01978   0.01022  -0.0009   0.4285   1.0000
   5.000   0.5581   0.02044   0.01053   0.0015   0.3272   1.0000
   5.250   0.5708   0.02194   0.01123   0.0035   0.2129   1.0000
   5.500   0.5857   0.02365   0.01248   0.0050   0.1555   1.0000
   5.750   0.6023   0.02517   0.01378   0.0064   0.1263   1.0000
   6.000   0.6203   0.02656   0.01518   0.0078   0.1076   1.0000
   6.250   0.6390   0.02795   0.01662   0.0092   0.0945   1.0000
   6.500   0.6582   0.02941   0.01803   0.0105   0.0846   1.0000
   6.750   0.6804   0.03094   0.01978   0.0117   0.0771   1.0000
   7.000   0.7014   0.03261   0.02147   0.0127   0.0704   1.0000
   7.250   0.7240   0.03450   0.02365   0.0137   0.0652   1.0000
   7.500   0.7452   0.03652   0.02581   0.0146   0.0614   1.0000
   7.750   0.7643   0.03892   0.02850   0.0156   0.0577   1.0000
   8.000   0.7808   0.04143   0.03147   0.0168   0.0542   1.0000
   8.250   0.7956   0.04430   0.03472   0.0180   0.0524   1.0000
   8.500   0.8077   0.04734   0.03809   0.0192   0.0510   1.0000
   8.750   0.8179   0.05023   0.04123   0.0203   0.0494   1.0000
   9.000   0.8261   0.05351   0.04460   0.0212   0.0478   1.0000
   9.250   0.8225   0.05723   0.04885   0.0227   0.0469   1.0000
   9.500   0.8144   0.06118   0.05320   0.0238   0.0463   1.0000
   9.750   0.8023   0.06521   0.05751   0.0246   0.0460   1.0000
  10.000   0.7851   0.06913   0.06162   0.0252   0.0460   1.0000
  10.250   0.7652   0.07369   0.06629   0.0242   0.0461   1.0000
  10.500   0.7461   0.07911   0.07180   0.0214   0.0464   1.0000
  10.750   0.7297   0.08521   0.07795   0.0174   0.0469   1.0000
  11.000   0.7155   0.09187   0.08461   0.0130   0.0472   1.0000
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