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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 1,000,000
Max Cl/Cd: 57.71 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e230-il-1000000.txt
Download as CSV file: xf-e230-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -1.0672   0.04689   0.04415  -0.0010   1.0000   0.0081
 -11.250  -1.0991   0.04212   0.03912   0.0023   1.0000   0.0077
 -11.000  -1.1617   0.03363   0.02981   0.0115   1.0000   0.0067
 -10.750  -1.1515   0.03236   0.02847   0.0133   1.0000   0.0069
 -10.500  -1.1474   0.02975   0.02557   0.0159   1.0000   0.0068
 -10.250  -1.1355   0.02807   0.02374   0.0177   1.0000   0.0070
 -10.000  -1.1220   0.02637   0.02187   0.0194   1.0000   0.0070
  -9.750  -1.1063   0.02486   0.02021   0.0209   1.0000   0.0072
  -9.500  -1.0888   0.02356   0.01877   0.0221   1.0000   0.0073
  -9.250  -1.0710   0.02210   0.01717   0.0235   1.0000   0.0074
  -9.000  -1.0520   0.02083   0.01576   0.0247   1.0000   0.0074
  -8.750  -1.0321   0.01966   0.01447   0.0258   1.0000   0.0075
  -8.500  -1.0114   0.01864   0.01336   0.0268   1.0000   0.0076
  -8.250  -0.9906   0.01762   0.01225   0.0279   1.0000   0.0077
  -8.000  -0.9691   0.01671   0.01126   0.0288   1.0000   0.0078
  -7.750  -0.9474   0.01585   0.01032   0.0298   1.0000   0.0079
  -7.500  -0.9247   0.01511   0.00951   0.0306   1.0000   0.0081
  -7.250  -0.9012   0.01448   0.00882   0.0313   1.0000   0.0083
  -7.000  -0.8771   0.01391   0.00820   0.0319   1.0000   0.0085
  -6.750  -0.8531   0.01332   0.00755   0.0325   1.0000   0.0086
  -6.500  -0.8321   0.01227   0.00639   0.0337   1.0000   0.0090
  -6.250  -0.8080   0.01163   0.00569   0.0343   1.0000   0.0096
  -6.000  -0.7823   0.01117   0.00520   0.0346   1.0000   0.0101
  -5.750  -0.7561   0.01078   0.00477   0.0349   1.0000   0.0107
  -5.500  -0.7268   0.01043   0.00438   0.0344   0.9868   0.0114
  -5.250  -0.6955   0.01009   0.00399   0.0337   0.9674   0.0126
  -5.000  -0.6724   0.00982   0.00369   0.0348   0.9494   0.0157
  -4.750  -0.6536   0.00915   0.00324   0.0367   0.9339   0.0590
  -4.500  -0.6327   0.00861   0.00292   0.0380   0.9204   0.1059
  -4.250  -0.6098   0.00822   0.00268   0.0390   0.9077   0.1438
  -4.000  -0.5865   0.00785   0.00245   0.0399   0.8955   0.1856
  -3.750  -0.5620   0.00756   0.00226   0.0406   0.8836   0.2195
  -3.500  -0.5373   0.00730   0.00209   0.0412   0.8715   0.2535
  -3.250  -0.5125   0.00700   0.00192   0.0418   0.8592   0.2966
  -3.000  -0.4875   0.00670   0.00177   0.0424   0.8466   0.3414
  -2.750  -0.4627   0.00640   0.00163   0.0430   0.8340   0.3933
  -2.500  -0.4372   0.00616   0.00151   0.0435   0.8210   0.4347
  -2.250  -0.4111   0.00598   0.00140   0.0439   0.8078   0.4688
  -2.000  -0.3851   0.00582   0.00130   0.0443   0.7940   0.5028
  -1.750  -0.3592   0.00564   0.00121   0.0448   0.7800   0.5397
  -1.500  -0.3332   0.00549   0.00113   0.0452   0.7657   0.5764
  -1.250  -0.3072   0.00534   0.00106   0.0457   0.7507   0.6114
  -1.000  -0.2812   0.00521   0.00101   0.0462   0.7355   0.6460
  -0.750  -0.2552   0.00509   0.00096   0.0467   0.7198   0.6802
  -0.500  -0.2294   0.00498   0.00092   0.0472   0.7036   0.7135
  -0.250  -0.2035   0.00488   0.00089   0.0478   0.6868   0.7466
   0.000  -0.1777   0.00479   0.00087   0.0483   0.6694   0.7793
   0.250  -0.1517   0.00473   0.00085   0.0489   0.6513   0.8104
   0.500  -0.1254   0.00468   0.00086   0.0494   0.6327   0.8401
   0.750  -0.0984   0.00465   0.00087   0.0498   0.6127   0.8669
   1.000  -0.0702   0.00466   0.00090   0.0499   0.5921   0.8913
   1.250  -0.0399   0.00471   0.00095   0.0495   0.5708   0.9126
   1.500  -0.0072   0.00482   0.00103   0.0486   0.5474   0.9292
   1.750   0.0281   0.00496   0.00112   0.0470   0.5223   0.9403
   2.000   0.0626   0.00513   0.00122   0.0457   0.4961   0.9485
   2.250   0.0925   0.00531   0.00131   0.0453   0.4711   0.9577
   2.500   0.1279   0.00550   0.00143   0.0437   0.4435   0.9614
   2.750   0.1627   0.00572   0.00155   0.0422   0.4137   0.9651
   3.000   0.1903   0.00597   0.00168   0.0423   0.3769   0.9719
   3.250   0.2274   0.00625   0.00181   0.0402   0.3343   0.9735
   3.500   0.2636   0.00655   0.00196   0.0382   0.2915   0.9755
   3.750   0.2985   0.00687   0.00211   0.0365   0.2471   0.9781
   4.000   0.3309   0.00723   0.00229   0.0354   0.2037   0.9815
   4.250   0.3622   0.00758   0.00250   0.0345   0.1662   0.9847
   4.500   0.3983   0.00794   0.00269   0.0324   0.1255   0.9859
   4.750   0.4335   0.00836   0.00292   0.0305   0.0855   0.9875
   5.000   0.4675   0.00898   0.00328   0.0288   0.0356   0.9893
   5.250   0.5013   0.00949   0.00367   0.0273   0.0163   0.9915
   5.500   0.5346   0.00980   0.00401   0.0260   0.0146   0.9936
   5.750   0.5687   0.01011   0.00437   0.0246   0.0137   0.9951
   6.000   0.6034   0.01050   0.00479   0.0229   0.0127   0.9964
   6.250   0.6371   0.01104   0.00540   0.0214   0.0119   0.9979
   6.500   0.6702   0.01178   0.00625   0.0200   0.0113   0.9993
   6.750   0.6994   0.01217   0.00668   0.0194   0.0110   1.0000
   7.000   0.7219   0.01269   0.00726   0.0202   0.0108   1.0000
   7.250   0.7440   0.01326   0.00789   0.0211   0.0106   1.0000
   7.500   0.7656   0.01391   0.00860   0.0220   0.0104   1.0000
   7.750   0.7868   0.01456   0.00933   0.0230   0.0102   1.0000
   8.000   0.8071   0.01537   0.01022   0.0241   0.0101   1.0000
   8.250   0.8272   0.01616   0.01108   0.0252   0.0099   1.0000
   8.500   0.8468   0.01697   0.01197   0.0264   0.0097   1.0000
   8.750   0.8658   0.01786   0.01294   0.0276   0.0095   1.0000
   9.000   0.8842   0.01880   0.01397   0.0289   0.0093   1.0000
   9.250   0.9021   0.01974   0.01499   0.0302   0.0090   1.0000
   9.500   0.9184   0.02089   0.01623   0.0316   0.0089   1.0000
   9.750   0.9333   0.02222   0.01767   0.0332   0.0088   1.0000
  10.000   0.9463   0.02378   0.01937   0.0349   0.0087   1.0000
  10.250   0.9550   0.02592   0.02167   0.0370   0.0085   1.0000
  10.500   0.9595   0.02844   0.02441   0.0393   0.0084   1.0000
  10.750   0.9593   0.03123   0.02743   0.0419   0.0083   1.0000
  11.000   0.9577   0.03364   0.03005   0.0445   0.0083   1.0000
  11.250   0.9548   0.03572   0.03230   0.0471   0.0083   1.0000
  11.500   0.9430   0.03743   0.03414   0.0509   0.0083   1.0000
  11.750   0.9327   0.03949   0.03633   0.0530   0.0084   1.0000
  12.000   0.9267   0.04177   0.03874   0.0534   0.0084   1.0000
  12.250   0.9169   0.04505   0.04217   0.0526   0.0084   1.0000
  12.500   0.8960   0.05051   0.04781   0.0498   0.0084   1.0000
  12.750   0.8946   0.05385   0.05125   0.0473   0.0085   1.0000
  13.000   0.8773   0.06027   0.05784   0.0426   0.0085   1.0000
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