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EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 420 AIRFOIL (e420-il)
Reynolds number: 200,000
Max Cl/Cd: 63.27 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e420-il-200000.txt
Download as CSV file: xf-e420-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 420 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.3845   0.09803   0.09329  -0.1659   0.7911   0.0386
 -10.000   0.3892   0.09686   0.09200  -0.1678   0.7737   0.0388
  -9.750   0.4071   0.09355   0.08856  -0.1676   0.7591   0.0392
  -9.500   0.4194   0.09155   0.08642  -0.1682   0.7467   0.0397
  -9.250   0.4280   0.08979   0.08462  -0.1681   0.7345   0.0405
  -9.000   0.4381   0.08804   0.08277  -0.1687   0.7248   0.0411
  -8.750   0.4450   0.08634   0.08104  -0.1688   0.7149   0.0423
  -8.500   0.4519   0.08484   0.07944  -0.1699   0.7071   0.0432
  -8.250   0.4478   0.08424   0.07888  -0.1708   0.6989   0.0436
  -8.000   0.4643   0.08128   0.07585  -0.1701   0.6912   0.0440
  -7.750   0.4772   0.07936   0.07385  -0.1702   0.6844   0.0445
  -7.500   0.4854   0.07772   0.07224  -0.1697   0.6771   0.0456
  -7.250   0.4935   0.07612   0.07059  -0.1697   0.6708   0.0467
  -7.000   0.5001   0.07456   0.06896  -0.1706   0.6654   0.0482
  -6.750   0.4907   0.07403   0.06853  -0.1708   0.6599   0.0487
  -6.500   0.5064   0.07136   0.06584  -0.1700   0.6544   0.0493
  -6.250   0.5182   0.06962   0.06406  -0.1696   0.6496   0.0499
  -6.000   0.5287   0.06806   0.06244  -0.1696   0.6451   0.0511
  -5.750   0.5306   0.06680   0.06125  -0.1683   0.6404   0.0524
  -5.500   0.5251   0.06599   0.06049  -0.1692   0.6359   0.0543
  -5.250   0.5322   0.06405   0.05855  -0.1707   0.6319   0.0548
  -5.000   0.5485   0.06212   0.05655  -0.1693   0.6279   0.0557
  -4.750   0.5603   0.06062   0.05505  -0.1695   0.6239   0.0571
  -4.500   0.5696   0.05905   0.05353  -0.1704   0.6198   0.0591
  -4.250   0.5851   0.05651   0.05100  -0.1770   0.6160   0.0612
  -4.000   0.5980   0.05500   0.04947  -0.1749   0.6125   0.0624
  -3.750   0.6170   0.05328   0.04770  -0.1765   0.6093   0.0646
  -3.500   0.6528   0.04990   0.04418  -0.1868   0.6062   0.0685
  -3.250   0.7356   0.03061   0.02430  -0.2196   0.6040   0.0433
  -3.000   0.7963   0.02316   0.01555  -0.2327   0.6005   0.0430
  -2.750   0.8282   0.02179   0.01384  -0.2342   0.5970   0.0446
  -2.500   0.8591   0.02104   0.01283  -0.2350   0.5935   0.0478
  -2.250   0.8903   0.02048   0.01208  -0.2358   0.5904   0.0529
  -2.000   0.9224   0.02029   0.01174  -0.2367   0.5875   0.0624
  -1.750   0.9500   0.02022   0.01162  -0.2368   0.5847   0.0751
  -1.500   0.9753   0.02021   0.01172  -0.2364   0.5816   0.0887
  -1.250   1.0018   0.02035   0.01180  -0.2362   0.5786   0.1045
  -1.000   1.0290   0.02043   0.01188  -0.2361   0.5757   0.1190
  -0.750   1.0571   0.02056   0.01196  -0.2362   0.5730   0.1329
  -0.500   1.0864   0.02074   0.01206  -0.2364   0.5704   0.1465
  -0.250   1.1170   0.02095   0.01223  -0.2371   0.5679   0.1600
   0.000   1.1418   0.02112   0.01243  -0.2366   0.5654   0.1717
   0.250   1.1654   0.02129   0.01258  -0.2359   0.5628   0.1844
   0.500   1.1894   0.02150   0.01285  -0.2352   0.5601   0.1962
   0.750   1.2149   0.02164   0.01299  -0.2349   0.5576   0.2084
   1.000   1.2417   0.02185   0.01311  -0.2348   0.5550   0.2218
   1.250   1.2696   0.02194   0.01321  -0.2349   0.5527   0.2347
   1.500   1.2993   0.02208   0.01328  -0.2354   0.5505   0.2480
   1.750   1.3300   0.02242   0.01351  -0.2361   0.5483   0.2624
   2.000   1.3518   0.02273   0.01392  -0.2352   0.5462   0.2747
   2.250   1.3725   0.02301   0.01430  -0.2341   0.5438   0.2867
   2.500   1.3942   0.02333   0.01467  -0.2331   0.5413   0.3002
   2.750   1.4169   0.02359   0.01499  -0.2324   0.5387   0.3143
   3.000   1.4413   0.02379   0.01524  -0.2319   0.5363   0.3294
   3.250   1.4680   0.02398   0.01545  -0.2319   0.5341   0.3472
   3.500   1.4964   0.02420   0.01568  -0.2322   0.5322   0.3686
   3.750   1.5262   0.02447   0.01599  -0.2329   0.5304   0.3962
   4.000   1.5529   0.02492   0.01656  -0.2331   0.5284   0.4388
   4.250   1.5627   0.02470   0.01719  -0.2299   0.5260   1.0000
   4.500   1.5796   0.02526   0.01774  -0.2282   0.5233   1.0000
   4.750   1.5981   0.02580   0.01828  -0.2268   0.5206   1.0000
   5.000   1.6192   0.02630   0.01876  -0.2259   0.5183   1.0000
   5.250   1.6424   0.02675   0.01919  -0.2253   0.5162   1.0000
   5.500   1.6681   0.02712   0.01950  -0.2252   0.5142   1.0000
   5.750   1.6978   0.02746   0.01977  -0.2258   0.5123   1.0000
   6.000   1.7303   0.02801   0.02024  -0.2270   0.5104   1.0000
   6.250   1.7342   0.02894   0.02132  -0.2232   0.5079   1.0000
   6.500   1.7388   0.02988   0.02240  -0.2196   0.5050   1.0000
   6.750   1.7496   0.03064   0.02323  -0.2171   0.5021   1.0000
   7.000   1.7660   0.03121   0.02382  -0.2155   0.4994   1.0000
   7.250   1.7883   0.03162   0.02423  -0.2149   0.4972   1.0000
   7.500   1.8156   0.03191   0.02451  -0.2151   0.4952   1.0000
   7.750   1.8490   0.03214   0.02468  -0.2164   0.4933   1.0000
   8.000   1.8708   0.03290   0.02546  -0.2159   0.4910   1.0000
   8.250   1.8309   0.03487   0.02770  -0.2051   0.4870   1.0000
   8.500   1.8172   0.03636   0.02932  -0.1990   0.4834   1.0000
   8.750   1.8274   0.03708   0.03010  -0.1966   0.4804   1.0000
   9.000   1.8547   0.03721   0.03022  -0.1968   0.4783   1.0000
   9.250   1.8942   0.03692   0.02989  -0.1988   0.4763   1.0000
   9.500   1.9436   0.03660   0.02950  -0.2026   0.4745   1.0000
   9.750   1.6999   0.05103   0.04461  -0.1709   0.4611   1.0000
  10.000   1.7553   0.04870   0.04223  -0.1731   0.4607   1.0000
  10.250   1.8121   0.04655   0.04003  -0.1758   0.4599   1.0000
  10.500   1.8715   0.04446   0.03789  -0.1792   0.4589   1.0000
  10.750   1.9316   0.04264   0.03600  -0.1830   0.4576   1.0000
  11.000   2.0034   0.04084   0.03410  -0.1889   0.4560   1.0000
  11.250   1.7436   0.06024   0.05408  -0.1627   0.4398   1.0000
  11.500   1.8039   0.05672   0.05054  -0.1644   0.4399   1.0000
  11.750   1.8691   0.05317   0.04695  -0.1668   0.4398   1.0000
  12.000   1.9422   0.04947   0.04320  -0.1705   0.4393   1.0000
  12.250   1.3858   0.12053   0.11494  -0.1576   0.3617   1.0000
  12.500   1.4134   0.11951   0.11394  -0.1569   0.3609   1.0000
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