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EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 398 AIRFOIL (e398-il)
Reynolds number: 500,000
Max Cl/Cd: 128.99 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e398-il-500000.txt
Download as CSV file: xf-e398-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 398 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5134   0.07149   0.06885  -0.0789   0.9972   0.0094
 -12.250  -0.5332   0.06021   0.05734  -0.0911   0.9932   0.0094
 -12.000  -0.5425   0.05126   0.04816  -0.1018   0.9869   0.0091
 -11.750  -0.5422   0.04380   0.04049  -0.1122   0.9793   0.0092
 -11.500  -0.5344   0.03748   0.03395  -0.1220   0.9699   0.0092
 -11.250  -0.5249   0.03214   0.02837  -0.1307   0.9569   0.0093
 -11.000  -0.5003   0.02765   0.02361  -0.1409   0.9454   0.0094
 -10.750  -0.4731   0.02495   0.02065  -0.1464   0.9349   0.0097
 -10.500  -0.4441   0.02289   0.01837  -0.1504   0.9247   0.0100
 -10.250  -0.4158   0.02136   0.01659  -0.1530   0.9134   0.0105
 -10.000  -0.3950   0.01983   0.01486  -0.1540   0.8996   0.0108
  -9.750  -0.3754   0.01855   0.01344  -0.1543   0.8866   0.0113
  -9.500  -0.3529   0.01770   0.01247  -0.1545   0.8754   0.0119
  -9.250  -0.3294   0.01690   0.01150  -0.1546   0.8652   0.0126
  -9.000  -0.3064   0.01609   0.01054  -0.1545   0.8546   0.0135
  -8.750  -0.2831   0.01527   0.00962  -0.1546   0.8451   0.0148
  -8.500  -0.2580   0.01461   0.00881  -0.1547   0.8365   0.0169
  -8.250  -0.2329   0.01404   0.00816  -0.1547   0.8278   0.0199
  -8.000  -0.2066   0.01355   0.00757  -0.1548   0.8200   0.0245
  -7.750  -0.1811   0.01298   0.00698  -0.1549   0.8116   0.0306
  -7.500  -0.1542   0.01260   0.00652  -0.1550   0.8043   0.0365
  -7.250  -0.1273   0.01230   0.00617  -0.1550   0.7967   0.0423
  -7.000  -0.1002   0.01196   0.00579  -0.1552   0.7898   0.0492
  -6.750  -0.0730   0.01164   0.00546  -0.1554   0.7829   0.0568
  -6.500  -0.0456   0.01136   0.00514  -0.1555   0.7759   0.0652
  -6.250  -0.0178   0.01111   0.00484  -0.1557   0.7696   0.0746
  -6.000   0.0099   0.01087   0.00458  -0.1558   0.7629   0.0851
  -5.750   0.0380   0.01067   0.00432  -0.1560   0.7571   0.0967
  -5.500   0.0659   0.01045   0.00410  -0.1562   0.7510   0.1098
  -5.250   0.0939   0.01024   0.00389  -0.1564   0.7449   0.1241
  -5.000   0.1224   0.01008   0.00369  -0.1566   0.7395   0.1394
  -4.750   0.1505   0.00989   0.00354  -0.1568   0.7338   0.1554
  -4.500   0.1788   0.00975   0.00339  -0.1570   0.7283   0.1719
  -4.250   0.2074   0.00964   0.00326  -0.1573   0.7233   0.1896
  -4.000   0.2357   0.00950   0.00316  -0.1574   0.7178   0.2079
  -3.750   0.2641   0.00941   0.00306  -0.1576   0.7127   0.2265
  -3.500   0.2930   0.00937   0.00298  -0.1579   0.7082   0.2447
  -3.250   0.3213   0.00928   0.00293  -0.1581   0.7031   0.2629
  -3.000   0.3498   0.00921   0.00287  -0.1582   0.6982   0.2811
  -2.750   0.3786   0.00918   0.00281  -0.1585   0.6938   0.2990
  -2.500   0.4071   0.00914   0.00280  -0.1587   0.6894   0.3166
  -2.250   0.4355   0.00909   0.00277  -0.1589   0.6847   0.3339
  -2.000   0.4641   0.00906   0.00274  -0.1591   0.6802   0.3516
  -1.750   0.4930   0.00908   0.00274  -0.1593   0.6762   0.3696
  -1.500   0.5213   0.00904   0.00275  -0.1595   0.6718   0.3872
  -1.250   0.5498   0.00902   0.00275  -0.1596   0.6674   0.4056
  -1.000   0.5784   0.00903   0.00276  -0.1598   0.6634   0.4249
  -0.750   0.6071   0.00906   0.00280  -0.1600   0.6595   0.4445
  -0.500   0.6353   0.00903   0.00284  -0.1602   0.6552   0.4644
  -0.250   0.6637   0.00902   0.00287  -0.1603   0.6510   0.4854
   0.000   0.6923   0.00905   0.00291  -0.1605   0.6472   0.5079
   0.250   0.7207   0.00907   0.00298  -0.1607   0.6433   0.5306
   0.500   0.7487   0.00906   0.00306  -0.1608   0.6391   0.5549
   0.750   0.7768   0.00907   0.00312  -0.1609   0.6351   0.5799
   1.000   0.8053   0.00911   0.00319  -0.1610   0.6313   0.6063
   1.250   0.8333   0.00915   0.00330  -0.1611   0.6274   0.6335
   1.500   0.8608   0.00915   0.00340  -0.1611   0.6233   0.6613
   1.750   0.8884   0.00917   0.00349  -0.1610   0.6192   0.6909
   2.000   0.9161   0.00922   0.00359  -0.1610   0.6154   0.7208
   2.250   0.9431   0.00925   0.00372  -0.1608   0.6114   0.7522
   2.500   0.9691   0.00925   0.00384  -0.1605   0.6070   0.7855
   2.750   0.9946   0.00925   0.00394  -0.1599   0.6029   0.8213
   3.000   1.0188   0.00930   0.00404  -0.1590   0.5989   0.8619
   3.250   1.0372   0.00921   0.00411  -0.1568   0.5946   0.9191
   3.500   1.0644   0.00918   0.00413  -0.1567   0.5898   1.0000
   3.750   1.0926   0.00930   0.00422  -0.1569   0.5852   1.0000
   4.000   1.1206   0.00945   0.00435  -0.1571   0.5805   1.0000
   4.250   1.1475   0.00953   0.00447  -0.1570   0.5751   1.0000
   4.500   1.1746   0.00965   0.00456  -0.1570   0.5698   1.0000
   4.750   1.2015   0.00978   0.00470  -0.1569   0.5642   1.0000
   5.000   1.2276   0.00988   0.00483  -0.1566   0.5581   1.0000
   5.250   1.2543   0.01003   0.00496  -0.1565   0.5527   1.0000
   5.500   1.2798   0.01014   0.00512  -0.1562   0.5463   1.0000
   5.750   1.3051   0.01027   0.00525  -0.1558   0.5392   1.0000
   6.000   1.3301   0.01041   0.00542  -0.1553   0.5320   1.0000
   6.250   1.3546   0.01054   0.00558  -0.1548   0.5243   1.0000
   6.500   1.3788   0.01071   0.00576  -0.1542   0.5165   1.0000
   6.750   1.4022   0.01088   0.00594  -0.1535   0.5076   1.0000
   7.000   1.4253   0.01105   0.00615  -0.1527   0.4978   1.0000
   7.250   1.4473   0.01127   0.00637  -0.1517   0.4880   1.0000
   7.500   1.4683   0.01150   0.00661  -0.1505   0.4762   1.0000
   7.750   1.4885   0.01175   0.00688  -0.1492   0.4632   1.0000
   8.000   1.5066   0.01206   0.00718  -0.1476   0.4479   1.0000
   8.250   1.5209   0.01244   0.00752  -0.1452   0.4307   1.0000
   8.500   1.5324   0.01289   0.00792  -0.1423   0.4115   1.0000
   8.750   1.5420   0.01345   0.00841  -0.1392   0.3885   1.0000
   9.000   1.5489   0.01416   0.00903  -0.1357   0.3646   1.0000
   9.250   1.5541   0.01499   0.00976  -0.1322   0.3393   1.0000
   9.500   1.5581   0.01594   0.01060  -0.1286   0.3136   1.0000
   9.750   1.5598   0.01707   0.01162  -0.1249   0.2885   1.0000
  10.000   1.5607   0.01833   0.01278  -0.1213   0.2638   1.0000
  10.250   1.5609   0.01975   0.01409  -0.1179   0.2396   1.0000
  10.500   1.5594   0.02138   0.01562  -0.1146   0.2166   1.0000
  10.750   1.5592   0.02306   0.01721  -0.1117   0.1944   1.0000
  11.000   1.5577   0.02493   0.01899  -0.1089   0.1744   1.0000
  11.250   1.5576   0.02684   0.02083  -0.1064   0.1556   1.0000
  11.500   1.5573   0.02886   0.02279  -0.1042   0.1382   1.0000
  11.750   1.5563   0.03103   0.02490  -0.1021   0.1221   1.0000
  12.000   1.5563   0.03323   0.02705  -0.1002   0.1082   1.0000
  12.250   1.5565   0.03549   0.02927  -0.0986   0.0956   1.0000
  12.500   1.5565   0.03786   0.03162  -0.0970   0.0837   1.0000
  12.750   1.5568   0.04029   0.03403  -0.0957   0.0731   1.0000
  13.000   1.5572   0.04279   0.03653  -0.0945   0.0640   1.0000
  13.250   1.5572   0.04543   0.03915  -0.0934   0.0559   1.0000
  13.500   1.5564   0.04823   0.04194  -0.0924   0.0484   1.0000
  13.750   1.5570   0.05097   0.04469  -0.0916   0.0423   1.0000
  14.000   1.5579   0.05374   0.04750  -0.0910   0.0370   1.0000
  14.250   1.5576   0.05674   0.05051  -0.0904   0.0327   1.0000
  14.500   1.5583   0.05968   0.05350  -0.0899   0.0291   1.0000
  14.750   1.5588   0.06274   0.05661  -0.0896   0.0261   1.0000
  15.000   1.5586   0.06594   0.05986  -0.0894   0.0235   1.0000
  15.250   1.5591   0.06913   0.06312  -0.0893   0.0213   1.0000
  15.500   1.5593   0.07242   0.06646  -0.0893   0.0193   1.0000
  15.750   1.5573   0.07609   0.07020  -0.0895   0.0176   1.0000
  16.000   1.5582   0.07942   0.07361  -0.0897   0.0160   1.0000
  16.250   1.5536   0.08361   0.07786  -0.0901   0.0147   1.0000
  16.500   1.5545   0.08705   0.08140  -0.0905   0.0135   1.0000
  16.750   1.5531   0.09088   0.08532  -0.0911   0.0124   1.0000
  17.000   1.5471   0.09550   0.09001  -0.0920   0.0115   1.0000
  17.250   1.5474   0.09920   0.09382  -0.0928   0.0106   1.0000
  17.500   1.5454   0.10330   0.09801  -0.0938   0.0099   1.0000
  17.750   1.5386   0.10824   0.10303  -0.0951   0.0093   1.0000
  18.000   1.5338   0.11293   0.10784  -0.0965   0.0088   1.0000
  18.250   1.5318   0.11718   0.11220  -0.0979   0.0083   1.0000
  18.500   1.5289   0.12163   0.11674  -0.0994   0.0078   1.0000
  18.750   1.5243   0.12640   0.12161  -0.1012   0.0074   1.0000
  19.000   1.5148   0.13207   0.12736  -0.1036   0.0071   1.0000
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