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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 200,000
Max Cl/Cd: 62.96 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e421-il-200000.txt
Download as CSV file: xf-e421-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 421 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2215   0.09614   0.09176  -0.1297   0.7926   0.0447
  -9.500   0.2343   0.09396   0.08941  -0.1303   0.7708   0.0452
  -9.250   0.2440   0.09197   0.08729  -0.1305   0.7532   0.0464
  -9.000   0.2522   0.09004   0.08526  -0.1309   0.7386   0.0471
  -8.750   0.2569   0.08807   0.08319  -0.1318   0.7268   0.0491
  -8.500   0.2426   0.08688   0.08203  -0.1349   0.7164   0.0499
  -8.250   0.2644   0.08372   0.07873  -0.1335   0.7060   0.0504
  -8.000   0.2772   0.08165   0.07664  -0.1329   0.6954   0.0512
  -7.750   0.2871   0.07976   0.07465  -0.1331   0.6872   0.0525
  -7.500   0.2931   0.07783   0.07274  -0.1334   0.6783   0.0543
  -7.250   0.2817   0.07631   0.07122  -0.1360   0.6716   0.0562
  -7.000   0.2902   0.07361   0.06849  -0.1358   0.6647   0.0568
  -6.750   0.3049   0.07152   0.06638  -0.1349   0.6569   0.0575
  -6.500   0.3166   0.06978   0.06457  -0.1344   0.6506   0.0595
  -6.250   0.3178   0.06812   0.06293  -0.1346   0.6448   0.0620
  -6.000   0.3064   0.06536   0.06024  -0.1416   0.6398   0.0637
  -5.750   0.3270   0.06415   0.05897  -0.1358   0.6338   0.0657
  -5.500   0.3393   0.06230   0.05704  -0.1367   0.6290   0.0677
  -5.250   0.3473   0.05787   0.05264  -0.1490   0.6245   0.0720
  -5.000   0.3590   0.05636   0.05114  -0.1452   0.6190   0.0729
  -4.750   0.3747   0.04765   0.04231  -0.1555   0.6157   0.0559
  -4.500   0.3934   0.04699   0.04156  -0.1547   0.6110   0.0583
  -4.250   0.4371   0.02037   0.01225  -0.1828   0.6101   0.0444
  -4.000   0.4624   0.01993   0.01181  -0.1824   0.6047   0.0491
  -3.750   0.4893   0.01941   0.01121  -0.1823   0.5998   0.0549
  -3.500   0.5174   0.01892   0.01056  -0.1824   0.5956   0.0629
  -3.250   0.5465   0.01869   0.01023  -0.1826   0.5918   0.0734
  -3.000   0.5726   0.01859   0.01018  -0.1823   0.5876   0.0843
  -2.750   0.5993   0.01856   0.01014  -0.1821   0.5831   0.0960
  -2.500   0.6269   0.01852   0.01005  -0.1819   0.5790   0.1077
  -2.250   0.6554   0.01849   0.00990  -0.1819   0.5754   0.1195
  -2.000   0.6842   0.01863   0.00989  -0.1820   0.5719   0.1314
  -1.750   0.7096   0.01866   0.01002  -0.1815   0.5682   0.1421
  -1.500   0.7362   0.01863   0.01000  -0.1812   0.5645   0.1528
  -1.250   0.7639   0.01865   0.00990  -0.1811   0.5612   0.1647
  -1.000   0.7919   0.01872   0.00995  -0.1810   0.5580   0.1761
  -0.750   0.8210   0.01878   0.00990  -0.1812   0.5550   0.1875
  -0.500   0.8472   0.01897   0.01002  -0.1808   0.5518   0.1992
  -0.250   0.8723   0.01895   0.01011  -0.1803   0.5484   0.2098
   0.000   0.8988   0.01901   0.01012  -0.1801   0.5453   0.2215
   0.250   0.9258   0.01910   0.01021  -0.1799   0.5424   0.2332
   0.500   0.9538   0.01913   0.01019  -0.1799   0.5397   0.2447
   0.750   0.9830   0.01931   0.01024  -0.1801   0.5371   0.2576
   1.000   1.0094   0.01946   0.01045  -0.1799   0.5343   0.2696
   1.250   1.0331   0.01957   0.01064  -0.1792   0.5313   0.2818
   1.500   1.0581   0.01976   0.01085  -0.1787   0.5283   0.2952
   1.750   1.0838   0.01987   0.01103  -0.1784   0.5256   0.3094
   2.000   1.1107   0.01998   0.01117  -0.1783   0.5230   0.3251
   2.250   1.1387   0.02009   0.01128  -0.1784   0.5206   0.3437
   2.500   1.1680   0.02029   0.01146  -0.1787   0.5182   0.3668
   2.750   1.1920   0.02052   0.01184  -0.1782   0.5157   0.3938
   3.000   1.2138   0.02066   0.01223  -0.1773   0.5129   0.4370
   3.250   1.2356   0.02003   0.01257  -0.1761   0.5102   1.0000
   3.500   1.2605   0.02038   0.01284  -0.1757   0.5076   1.0000
   3.750   1.2865   0.02069   0.01306  -0.1754   0.5050   1.0000
   4.000   1.3143   0.02097   0.01325  -0.1754   0.5027   1.0000
   4.250   1.3436   0.02134   0.01350  -0.1758   0.5005   1.0000
   4.500   1.3682   0.02190   0.01404  -0.1755   0.4983   1.0000
   4.750   1.3870   0.02240   0.01463  -0.1741   0.4957   1.0000
   5.000   1.4073   0.02288   0.01516  -0.1730   0.4928   1.0000
   5.250   1.4297   0.02329   0.01558  -0.1722   0.4899   1.0000
   5.500   1.4543   0.02363   0.01591  -0.1718   0.4874   1.0000
   5.750   1.4805   0.02397   0.01621  -0.1716   0.4852   1.0000
   6.000   1.5091   0.02435   0.01653  -0.1720   0.4832   1.0000
   6.250   1.5364   0.02494   0.01709  -0.1722   0.4811   1.0000
   6.500   1.5479   0.02560   0.01791  -0.1697   0.4780   1.0000
   6.750   1.5642   0.02621   0.01861  -0.1680   0.4749   1.0000
   7.000   1.5838   0.02673   0.01918  -0.1669   0.4721   1.0000
   7.250   1.6074   0.02708   0.01955  -0.1664   0.4695   1.0000
   7.500   1.6341   0.02735   0.01979  -0.1664   0.4672   1.0000
   7.750   1.6651   0.02764   0.02002  -0.1672   0.4651   1.0000
   8.000   1.6818   0.02839   0.02087  -0.1657   0.4624   1.0000
   8.250   1.6864   0.02926   0.02191  -0.1622   0.4586   1.0000
   8.500   1.7001   0.02987   0.02261  -0.1603   0.4553   1.0000
   8.750   1.7222   0.03015   0.02292  -0.1595   0.4524   1.0000
   9.000   1.7504   0.03026   0.02300  -0.1598   0.4499   1.0000
   9.250   1.7864   0.03030   0.02297  -0.1613   0.4476   1.0000
   9.500   1.7888   0.03131   0.02416  -0.1577   0.4441   1.0000
   9.750   1.7845   0.03237   0.02538  -0.1530   0.4401   1.0000
  10.000   1.7953   0.03284   0.02592  -0.1505   0.4367   1.0000
  10.250   1.8218   0.03284   0.02593  -0.1504   0.4339   1.0000
  10.500   1.8626   0.03257   0.02560  -0.1527   0.4313   1.0000
  10.750   1.8741   0.03325   0.02635  -0.1505   0.4282   1.0000
  11.000   1.8387   0.03508   0.02842  -0.1414   0.4238   1.0000
  11.250   1.8411   0.03586   0.02928  -0.1381   0.4200   1.0000
  11.500   1.8701   0.03561   0.02903  -0.1383   0.4170   1.0000
  11.750   1.9248   0.03460   0.02793  -0.1421   0.4142   1.0000
  12.000   1.8934   0.03672   0.03027  -0.1345   0.4100   1.0000
  12.250   1.8546   0.03959   0.03334  -0.1272   0.4049   1.0000
  12.500   1.8786   0.03938   0.03316  -0.1267   0.4014   1.0000
  12.750   1.9359   0.03759   0.03128  -0.1298   0.3985   1.0000
  13.000   1.8984   0.04081   0.03470  -0.1234   0.3936   1.0000
  13.250   1.8484   0.04548   0.03957  -0.1174   0.3874   1.0000
  13.500   1.8926   0.04377   0.03784  -0.1183   0.3844   1.0000
  13.750   1.9638   0.04063   0.03458  -0.1218   0.3815   1.0000
  14.000   1.8093   0.05421   0.04859  -0.1109   0.3713   1.0000
  14.250   1.8696   0.05051   0.04486  -0.1119   0.3690   1.0000
  14.500   1.9407   0.04636   0.04061  -0.1139   0.3663   1.0000
  14.750   1.7005   0.07345   0.06816  -0.1070   0.3464   1.0000
  15.000   1.7739   0.06690   0.06160  -0.1067   0.3467   1.0000
  15.250   1.7695   0.06986   0.06463  -0.1062   0.3400   1.0000
  15.500   1.8355   0.06443   0.05917  -0.1060   0.3382   1.0000
  15.750   1.7557   0.07681   0.07171  -0.1055   0.3256   1.0000
  16.000   1.8161   0.07168   0.06655  -0.1050   0.3235   1.0000
  16.250   1.7570   0.08208   0.07709  -0.1052   0.3115   1.0000
  16.500   1.8120   0.07744   0.07241  -0.1044   0.3086   1.0000
  16.750   1.7647   0.08663   0.08172  -0.1050   0.2971   1.0000
  17.000   1.8183   0.08204   0.07706  -0.1041   0.2934   1.0000
  17.250   1.7733   0.09116   0.08631  -0.1049   0.2820   1.0000
  17.500   1.7873   0.09204   0.08719  -0.1047   0.2750   1.0000
  17.750   1.7849   0.09528   0.09044  -0.1049   0.2664   1.0000
  18.000   1.7712   0.10025   0.09548  -0.1055   0.2572   1.0000
  18.250   1.7988   0.09903   0.09416  -0.1049   0.2504   1.0000
  18.500   1.7711   0.10621   0.10146  -0.1062   0.2407   1.0000
  18.750   1.7834   0.10725   0.10246  -0.1061   0.2332   1.0000
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