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EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 435 AIRFOIL (e435-il)
Reynolds number: 500,000
Max Cl/Cd: 119.48 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e435-il-500000.txt
Download as CSV file: xf-e435-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 435 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1137   0.09379   0.09141  -0.1095   0.9489   0.0213
 -10.750  -0.1024   0.08781   0.08541  -0.1159   0.9448   0.0222
 -10.500  -0.1163   0.07167   0.06929  -0.1312   0.9374   0.0235
 -10.250  -0.1004   0.06423   0.06179  -0.1414   0.9322   0.0237
 -10.000  -0.0942   0.05547   0.05287  -0.1546   0.9210   0.0239
  -9.750  -0.0973   0.04879   0.04593  -0.1642   0.9030   0.0241
  -9.500  -0.1052   0.04520   0.04213  -0.1670   0.8852   0.0243
  -9.250  -0.1189   0.04261   0.03936  -0.1665   0.8698   0.0245
  -9.000  -0.1344   0.04073   0.03732  -0.1642   0.8574   0.0246
  -8.750  -0.1383   0.03862   0.03501  -0.1630   0.8487   0.0250
  -8.500  -0.1408   0.03648   0.03268  -0.1613   0.8403   0.0257
  -8.250  -0.1833   0.02344   0.01799  -0.1546   0.8313   0.0127
  -8.000  -0.1669   0.02156   0.01593  -0.1536   0.8259   0.0124
  -7.750  -0.1477   0.01978   0.01390  -0.1528   0.8213   0.0120
  -7.500  -0.1252   0.01841   0.01230  -0.1523   0.8172   0.0117
  -7.250  -0.1047   0.01730   0.01105  -0.1514   0.8127   0.0116
  -7.000  -0.0827   0.01639   0.01003  -0.1506   0.8082   0.0116
  -6.750  -0.0596   0.01563   0.00916  -0.1502   0.8043   0.0117
  -6.500  -0.0355   0.01497   0.00840  -0.1499   0.8006   0.0119
  -6.250  -0.0133   0.01436   0.00776  -0.1493   0.7966   0.0123
  -6.000   0.0105   0.01382   0.00716  -0.1490   0.7925   0.0127
  -5.750   0.0345   0.01316   0.00644  -0.1489   0.7888   0.0136
  -5.500   0.0614   0.01275   0.00598  -0.1492   0.7855   0.0150
  -5.250   0.0868   0.01230   0.00550  -0.1492   0.7820   0.0174
  -5.000   0.1128   0.01185   0.00506  -0.1492   0.7782   0.0239
  -4.750   0.1397   0.01135   0.00464  -0.1496   0.7746   0.0456
  -4.500   0.1675   0.01093   0.00436  -0.1502   0.7714   0.0787
  -4.250   0.1965   0.01049   0.00412  -0.1512   0.7682   0.1382
  -4.000   0.2234   0.00973   0.00382  -0.1521   0.7648   0.2557
  -3.750   0.2527   0.00862   0.00355  -0.1539   0.7613   0.4914
  -3.500   0.2819   0.00860   0.00361  -0.1542   0.7579   0.5534
  -3.250   0.3114   0.00868   0.00363  -0.1546   0.7548   0.5770
  -3.000   0.3415   0.00882   0.00369  -0.1551   0.7517   0.5931
  -2.750   0.3692   0.00892   0.00376  -0.1550   0.7484   0.6064
  -2.500   0.3971   0.00901   0.00385  -0.1550   0.7448   0.6163
  -2.250   0.4263   0.00911   0.00387  -0.1553   0.7414   0.6258
  -2.000   0.4550   0.00919   0.00393  -0.1554   0.7383   0.6325
  -1.750   0.4848   0.00936   0.00401  -0.1559   0.7351   0.6408
  -1.500   0.5111   0.00945   0.00415  -0.1555   0.7316   0.6488
  -1.250   0.5391   0.00958   0.00425  -0.1555   0.7279   0.6572
  -1.000   0.5672   0.00962   0.00428  -0.1556   0.7244   0.6625
  -0.750   0.5962   0.00968   0.00429  -0.1559   0.7212   0.6662
  -0.500   0.6249   0.00974   0.00432  -0.1562   0.7177   0.6695
  -0.250   0.6524   0.00975   0.00432  -0.1563   0.7138   0.6727
   0.000   0.6812   0.00976   0.00428  -0.1567   0.7098   0.6753
   0.250   0.7099   0.00974   0.00423  -0.1570   0.7062   0.6776
   0.500   0.7392   0.00980   0.00426  -0.1574   0.7026   0.6799
   0.750   0.7655   0.00979   0.00429  -0.1572   0.6984   0.6822
   1.000   0.7931   0.00980   0.00429  -0.1573   0.6940   0.6846
   1.250   0.8217   0.00982   0.00428  -0.1576   0.6900   0.6873
   1.500   0.8507   0.00989   0.00430  -0.1581   0.6859   0.6903
   1.750   0.8771   0.00990   0.00433  -0.1580   0.6809   0.6928
   2.000   0.9042   0.00987   0.00432  -0.1580   0.6761   0.6950
   2.250   0.9328   0.00991   0.00433  -0.1582   0.6719   0.6973
   2.500   0.9587   0.00994   0.00441  -0.1580   0.6668   0.6998
   2.750   0.9850   0.00996   0.00445  -0.1579   0.6615   0.7026
   3.000   1.0129   0.01000   0.00446  -0.1580   0.6565   0.7056
   3.250   1.0389   0.01006   0.00454  -0.1579   0.6508   0.7087
   3.500   1.0644   0.01006   0.00458  -0.1575   0.6447   0.7113
   3.750   1.0918   0.01012   0.00462  -0.1576   0.6391   0.7139
   4.000   1.1155   0.01015   0.00473  -0.1569   0.6322   0.7167
   4.250   1.1410   0.01021   0.00479  -0.1566   0.6256   0.7198
   4.500   1.1657   0.01028   0.00489  -0.1562   0.6184   0.7230
   4.750   1.1902   0.01036   0.00497  -0.1557   0.6106   0.7262
   5.000   1.2136   0.01043   0.00509  -0.1550   0.6026   0.7293
   5.250   1.2367   0.01053   0.00520  -0.1542   0.5941   0.7327
   5.500   1.2592   0.01063   0.00536  -0.1533   0.5849   0.7363
   5.750   1.2813   0.01079   0.00549  -0.1524   0.5755   0.7400
   6.000   1.3021   0.01091   0.00565  -0.1512   0.5644   0.7435
   6.250   1.3214   0.01106   0.00584  -0.1497   0.5528   0.7470
   6.500   1.3383   0.01125   0.00603  -0.1477   0.5402   0.7508
   6.750   1.3529   0.01148   0.00624  -0.1453   0.5267   0.7552
   7.000   1.3670   0.01177   0.00651  -0.1428   0.5122   0.7597
   7.250   1.3800   0.01209   0.00684  -0.1402   0.4967   0.7641
   7.500   1.3924   0.01247   0.00721  -0.1375   0.4799   0.7691
   7.750   1.4042   0.01292   0.00762  -0.1348   0.4624   0.7744
   8.000   1.4147   0.01340   0.00810  -0.1320   0.4441   0.7793
   8.250   1.4235   0.01398   0.00866  -0.1289   0.4251   0.7849
   8.500   1.4308   0.01468   0.00930  -0.1258   0.4052   0.7913
   8.750   1.4371   0.01543   0.01002  -0.1225   0.3865   0.7975
   9.000   1.4436   0.01626   0.01081  -0.1195   0.3670   0.8052
   9.250   1.4498   0.01714   0.01168  -0.1165   0.3476   0.8131
   9.500   1.4554   0.01813   0.01264  -0.1136   0.3284   0.8229
   9.750   1.4597   0.01920   0.01369  -0.1107   0.3097   0.8335
  10.000   1.4640   0.02033   0.01481  -0.1078   0.2921   0.8469
  10.250   1.4680   0.02148   0.01598  -0.1050   0.2753   0.8659
  10.500   1.4698   0.02256   0.01714  -0.1018   0.2595   0.9076
  10.750   1.4740   0.02378   0.01835  -0.0994   0.2429   1.0000
  11.000   1.4802   0.02523   0.01974  -0.0976   0.2258   1.0000
  11.250   1.4860   0.02675   0.02119  -0.0958   0.2098   1.0000
  11.500   1.4918   0.02831   0.02271  -0.0941   0.1948   1.0000
  11.750   1.4974   0.02993   0.02428  -0.0924   0.1803   1.0000
  12.000   1.5025   0.03163   0.02595  -0.0908   0.1667   1.0000
  12.250   1.5071   0.03342   0.02770  -0.0893   0.1535   1.0000
  12.500   1.5117   0.03528   0.02951  -0.0878   0.1406   1.0000
  12.750   1.5168   0.03712   0.03133  -0.0865   0.1283   1.0000
  13.000   1.5216   0.03906   0.03324  -0.0853   0.1168   1.0000
  13.250   1.5262   0.04106   0.03523  -0.0841   0.1062   1.0000
  13.500   1.5301   0.04318   0.03734  -0.0830   0.0967   1.0000
  13.750   1.5327   0.04547   0.03961  -0.0820   0.0875   1.0000
  14.000   1.5368   0.04768   0.04182  -0.0811   0.0793   1.0000
  14.250   1.5407   0.04997   0.04413  -0.0803   0.0719   1.0000
  14.500   1.5429   0.05251   0.04667  -0.0795   0.0652   1.0000
  14.750   1.5456   0.05503   0.04921  -0.0789   0.0590   1.0000
  15.000   1.5483   0.05763   0.05184  -0.0784   0.0534   1.0000
  15.250   1.5480   0.06064   0.05485  -0.0779   0.0482   1.0000
  15.500   1.5513   0.06328   0.05755  -0.0776   0.0437   1.0000
  15.750   1.5511   0.06642   0.06072  -0.0773   0.0400   1.0000
  16.000   1.5521   0.06946   0.06380  -0.0772   0.0361   1.0000
  16.250   1.5520   0.07271   0.06712  -0.0772   0.0333   1.0000
  16.500   1.5522   0.07600   0.07046  -0.0773   0.0304   1.0000
  16.750   1.5510   0.07956   0.07409  -0.0776   0.0280   1.0000
  17.000   1.5510   0.08298   0.07758  -0.0780   0.0256   1.0000
  17.250   1.5475   0.08697   0.08163  -0.0785   0.0238   1.0000
  17.500   1.5483   0.09040   0.08515  -0.0791   0.0219   1.0000
  17.750   1.5438   0.09470   0.08951  -0.0800   0.0204   1.0000
  18.000   1.5428   0.09851   0.09342  -0.0809   0.0189   1.0000
  18.250   1.5405   0.10254   0.09754  -0.0819   0.0176   1.0000
  18.500   1.5337   0.10736   0.10244  -0.0833   0.0166   1.0000
  18.750   1.5320   0.11142   0.10661  -0.0846   0.0156   1.0000
  19.000   1.5287   0.11576   0.11105  -0.0861   0.0147   1.0000
  19.250   1.5227   0.12062   0.11600  -0.0879   0.0139   1.0000
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