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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 100,000
Max Cl/Cd: 29.5 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e422-il-100000.txt
Download as CSV file: xf-e422-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 422 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1545   0.14064   0.13595  -0.0409   1.0000   0.0656
 -11.500  -0.1615   0.14028   0.13569  -0.0424   1.0000   0.0661
 -11.250  -0.1578   0.13730   0.13282  -0.0422   1.0000   0.0665
 -11.000  -0.1457   0.13333   0.12893  -0.0407   1.0000   0.0675
 -10.750  -0.1438   0.13139   0.12713  -0.0394   1.0000   0.0687
 -10.500  -0.1406   0.12969   0.12559  -0.0400   0.9963   0.0700
 -10.250  -0.1119   0.12489   0.12079  -0.0478   0.9852   0.0732
 -10.000  -0.1017   0.12300   0.11890  -0.0584   0.9650   0.0749
  -9.750  -0.0633   0.11550   0.11140  -0.0613   0.9471   0.0765
  -9.500  -0.0302   0.11051   0.10635  -0.0668   0.9277   0.0791
  -9.250  -0.0009   0.10613   0.10189  -0.0745   0.9085   0.0829
  -9.000   0.0051   0.10512   0.10079  -0.0879   0.8852   0.0850
  -8.750   0.0574   0.09682   0.09231  -0.0884   0.8654   0.0876
  -8.500   0.0786   0.09363   0.08893  -0.0913   0.8403   0.0909
  -8.250   0.0788   0.09262   0.08782  -0.0955   0.8186   0.0953
  -8.000   0.0698   0.09234   0.08748  -0.0996   0.8001   0.0960
  -7.750   0.1075   0.08633   0.08132  -0.0968   0.7857   0.0990
  -7.500   0.1194   0.08414   0.07903  -0.0970   0.7719   0.1029
  -7.250   0.1140   0.08332   0.07823  -0.0988   0.7585   0.1072
  -7.000   0.0909   0.08406   0.07898  -0.1038   0.7481   0.1083
  -6.750   0.1305   0.07806   0.07288  -0.0989   0.7375   0.1114
  -6.500   0.1404   0.07597   0.07075  -0.0985   0.7279   0.1150
  -6.250   0.1399   0.07465   0.06943  -0.0989   0.7188   0.1185
  -6.000   0.1306   0.07361   0.06837  -0.1074   0.7117   0.1223
  -5.750   0.1465   0.07024   0.06502  -0.1032   0.7028   0.1239
  -5.500   0.1614   0.06784   0.06252  -0.1022   0.6962   0.1267
  -5.250   0.1713   0.06589   0.06061  -0.1032   0.6884   0.1306
  -5.000   0.1805   0.06324   0.05785  -0.1126   0.6821   0.1373
  -4.750   0.1959   0.06044   0.05498  -0.1108   0.6769   0.1388
  -4.500   0.2099   0.04024   0.03396  -0.1300   0.6750   0.0672
  -4.250   0.2272   0.03543   0.02865  -0.1316   0.6683   0.0643
  -4.000   0.2484   0.03157   0.02410  -0.1323   0.6627   0.0636
  -3.750   0.2740   0.02891   0.02054  -0.1323   0.6581   0.0660
  -3.500   0.2950   0.02830   0.02006  -0.1315   0.6506   0.0707
  -3.250   0.3205   0.02678   0.01803  -0.1309   0.6451   0.0758
  -3.000   0.3480   0.02596   0.01692  -0.1305   0.6407   0.0849
  -2.750   0.3708   0.02562   0.01673  -0.1297   0.6348   0.0991
  -2.500   0.3952   0.02552   0.01665  -0.1288   0.6288   0.1247
  -2.250   0.4216   0.02592   0.01711  -0.1282   0.6240   0.1598
  -2.000   0.4468   0.02630   0.01744  -0.1275   0.6195   0.1910
  -1.750   0.4678   0.02670   0.01792  -0.1265   0.6138   0.2134
  -1.500   0.4923   0.02679   0.01795  -0.1258   0.6091   0.2341
  -1.250   0.5195   0.02668   0.01770  -0.1255   0.6051   0.2533
  -1.000   0.5448   0.02670   0.01761  -0.1250   0.6010   0.2695
  -0.750   0.5651   0.02695   0.01785  -0.1240   0.5954   0.2836
  -0.500   0.5901   0.02703   0.01782  -0.1234   0.5910   0.2991
  -0.250   0.6169   0.02701   0.01773  -0.1231   0.5875   0.3149
   0.000   0.6457   0.02698   0.01760  -0.1231   0.5846   0.3313
   0.250   0.6611   0.02765   0.01844  -0.1216   0.5792   0.3448
   0.500   0.6829   0.02799   0.01880  -0.1208   0.5744   0.3616
   0.750   0.7097   0.02804   0.01883  -0.1206   0.5708   0.3826
   1.000   0.7376   0.02809   0.01882  -0.1204   0.5679   0.4079
   1.250   0.7603   0.02859   0.01944  -0.1198   0.5645   0.4359
   1.500   0.7719   0.02969   0.02079  -0.1182   0.5591   0.4668
   1.750   0.7927   0.02984   0.02132  -0.1174   0.5550   0.5427
   2.000   0.8402   0.02913   0.02112  -0.1206   0.5517   1.0000
   2.250   0.8701   0.02949   0.02122  -0.1206   0.5492   1.0000
   2.500   0.8733   0.03152   0.02332  -0.1181   0.5445   1.0000
   2.750   0.8737   0.03371   0.02558  -0.1154   0.5390   1.0000
   3.000   0.8946   0.03450   0.02626  -0.1146   0.5354   1.0000
   3.250   0.9257   0.03466   0.02626  -0.1146   0.5329   1.0000
   3.500   0.9601   0.03473   0.02616  -0.1151   0.5309   1.0000
   3.750   0.8418   0.04543   0.03743  -0.1037   0.5181   1.0000
   4.000   0.8809   0.04501   0.03687  -0.1042   0.5160   1.0000
   4.250   0.9247   0.04424   0.03595  -0.1049   0.5145   1.0000
   4.500   0.9717   0.04332   0.03488  -0.1061   0.5133   1.0000
   4.750   0.6250   0.07803   0.07058  -0.0977   0.5206   1.0000
   5.000   0.6535   0.07898   0.07139  -0.0974   0.5160   1.0000
   5.250   0.6784   0.08065   0.07297  -0.0974   0.5142   1.0000
   5.500   0.6991   0.08289   0.07514  -0.0975   0.5132   1.0000
   5.750   0.7194   0.08544   0.07763  -0.0976   0.5126   1.0000
   6.000   0.6573   0.09384   0.08622  -0.0984   0.5319   1.0000
   6.250   0.6986   0.09663   0.08890  -0.0993   0.5301   1.0000
   7.000   0.6700   0.10269   0.09497  -0.0959   0.5043   1.0000
   7.250   0.6932   0.10441   0.09664  -0.0957   0.4987   1.0000
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