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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 100,000
Max Cl/Cd: 27.66 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e421-il-100000.txt
Download as CSV file: xf-e421-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0505   0.12343   0.11895  -0.0861   0.9253   0.0684
 -10.250   0.0709   0.11986   0.11536  -0.0918   0.9140   0.0708
 -10.000   0.0794   0.11907   0.11454  -0.1010   0.9019   0.0718
  -9.750   0.1283   0.11023   0.10562  -0.1037   0.8946   0.0744
  -9.500   0.1596   0.10591   0.10121  -0.1100   0.8817   0.0772
  -9.250   0.1743   0.10455   0.09974  -0.1191   0.8658   0.0808
  -9.000   0.2063   0.09895   0.09401  -0.1233   0.8509   0.0820
  -8.750   0.2369   0.09474   0.08964  -0.1264   0.8350   0.0851
  -8.500   0.2549   0.09214   0.08691  -0.1299   0.8197   0.0888
  -8.250   0.2539   0.09224   0.08691  -0.1341   0.8045   0.0911
  -8.000   0.2588   0.09003   0.08467  -0.1351   0.7902   0.0919
  -7.750   0.2863   0.08552   0.08005  -0.1344   0.7789   0.0939
  -7.500   0.2997   0.08330   0.07774  -0.1348   0.7678   0.0967
  -7.250   0.3053   0.08181   0.07623  -0.1352   0.7572   0.0999
  -7.000   0.2928   0.08238   0.07680  -0.1372   0.7481   0.1026
  -6.750   0.2821   0.08209   0.07658  -0.1382   0.7391   0.1033
  -6.500   0.3191   0.07642   0.07079  -0.1360   0.7314   0.1058
  -6.250   0.3314   0.07443   0.06874  -0.1357   0.7245   0.1086
  -6.000   0.3304   0.07341   0.06778  -0.1346   0.7162   0.1119
  -5.750   0.3211   0.07420   0.06856  -0.1419   0.7097   0.1159
  -5.500   0.3332   0.07062   0.06498  -0.1393   0.7037   0.1174
  -5.250   0.3465   0.06845   0.06284  -0.1358   0.6969   0.1208
  -5.000   0.3571   0.06695   0.06129  -0.1374   0.6914   0.1272
  -4.750   0.3699   0.06473   0.05899  -0.1444   0.6870   0.1319
  -4.500   0.3758   0.06300   0.05737  -0.1403   0.6806   0.1342
  -4.250   0.3885   0.06123   0.05559  -0.1401   0.6750   0.1382
  -4.000   0.4166   0.05845   0.05261  -0.1520   0.6704   0.1471
  -3.750   0.4469   0.04878   0.04262  -0.1626   0.6671   0.1023
  -3.500   0.4610   0.04625   0.04010  -0.1632   0.6611   0.1009
  -3.250   0.4928   0.04030   0.03380  -0.1700   0.6566   0.0982
  -3.000   0.5295   0.03524   0.02812  -0.1758   0.6528   0.1069
  -2.750   0.5626   0.03345   0.02590  -0.1779   0.6494   0.1198
  -2.500   0.5845   0.03230   0.02440  -0.1781   0.6444   0.1321
  -2.250   0.6047   0.03256   0.02470  -0.1769   0.6391   0.1432
  -2.000   0.6305   0.03231   0.02438  -0.1766   0.6348   0.1552
  -1.750   0.6618   0.03159   0.02337  -0.1774   0.6314   0.1694
  -1.500   0.6883   0.03123   0.02270  -0.1776   0.6279   0.1834
  -1.250   0.7013   0.03184   0.02346  -0.1755   0.6229   0.1927
  -1.000   0.7243   0.03176   0.02322  -0.1751   0.6187   0.2053
  -0.750   0.7526   0.03156   0.02276  -0.1752   0.6151   0.2205
  -0.500   0.7834   0.03140   0.02247  -0.1756   0.6121   0.2355
  -0.250   0.8036   0.03176   0.02283  -0.1747   0.6085   0.2471
   0.000   0.8112   0.03285   0.02388  -0.1722   0.6035   0.2577
   0.250   0.8278   0.03340   0.02452  -0.1708   0.5996   0.2690
   0.500   0.8550   0.03346   0.02447  -0.1708   0.5964   0.2835
   0.750   0.8867   0.03336   0.02423  -0.1713   0.5938   0.3000
   1.000   0.9209   0.03329   0.02401  -0.1721   0.5914   0.3177
   1.250   0.8879   0.03678   0.02784  -0.1648   0.5843   0.3176
   1.500   0.8901   0.03846   0.02959  -0.1620   0.5799   0.3272
   1.750   0.9183   0.03859   0.02967  -0.1620   0.5771   0.3442
   2.000   0.9563   0.03821   0.02920  -0.1632   0.5751   0.3662
   2.250   0.9966   0.03778   0.02871  -0.1647   0.5733   0.3912
   2.500   0.7817   0.05568   0.04711  -0.1437   0.5561   0.3324
   2.750   0.8352   0.05337   0.04479  -0.1446   0.5553   0.3587
   3.000   0.8932   0.05112   0.04246  -0.1465   0.5548   0.3909
   3.250   0.9552   0.04883   0.04016  -0.1492   0.5543   0.4333
   4.250   0.7621   0.08025   0.07194  -0.1375   0.5351   0.3974
   4.500   0.7726   0.08326   0.07501  -0.1376   0.5355   0.4166
   6.000   0.6938   0.10888   0.10129  -0.1360   0.5445   0.4845
   6.250   0.7158   0.10939   0.10258  -0.1355   0.5399   1.0000
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