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EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 398 AIRFOIL (e398-il)
Reynolds number: 200,000
Max Cl/Cd: 84.76 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e398-il-200000.txt
Download as CSV file: xf-e398-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3749   0.06883   0.06553  -0.0899   0.9785   0.0243
 -10.250  -0.3975   0.05578   0.05226  -0.1061   0.9677   0.0238
 -10.000  -0.4058   0.04676   0.04297  -0.1199   0.9544   0.0232
  -9.750  -0.4042   0.03880   0.03443  -0.1339   0.9410   0.0233
  -9.500  -0.3877   0.03396   0.02889  -0.1407   0.9324   0.0243
  -9.250  -0.3583   0.03087   0.02559  -0.1450   0.9283   0.0257
  -9.000  -0.3344   0.02922   0.02376  -0.1464   0.9195   0.0274
  -8.750  -0.3017   0.02643   0.02044  -0.1498   0.9153   0.0292
  -8.500  -0.2791   0.02457   0.01852  -0.1503   0.9066   0.0315
  -8.250  -0.2462   0.02308   0.01669  -0.1523   0.9011   0.0354
  -8.000  -0.2194   0.02191   0.01554  -0.1532   0.8937   0.0404
  -7.750  -0.1908   0.02077   0.01432  -0.1542   0.8865   0.0470
  -7.500  -0.1620   0.01984   0.01327  -0.1551   0.8797   0.0549
  -7.250  -0.1356   0.01904   0.01237  -0.1554   0.8717   0.0634
  -7.000  -0.1047   0.01832   0.01152  -0.1565   0.8661   0.0733
  -6.750  -0.0797   0.01799   0.01106  -0.1562   0.8573   0.0825
  -6.500  -0.0494   0.01728   0.01030  -0.1571   0.8517   0.0936
  -6.250  -0.0253   0.01677   0.00979  -0.1567   0.8433   0.1043
  -6.000   0.0040   0.01625   0.00920  -0.1572   0.8374   0.1175
  -5.750   0.0306   0.01585   0.00877  -0.1573   0.8306   0.1315
  -5.500   0.0583   0.01548   0.00836  -0.1574   0.8238   0.1473
  -5.250   0.0884   0.01516   0.00796  -0.1580   0.8187   0.1655
  -5.000   0.1138   0.01496   0.00773  -0.1577   0.8112   0.1835
  -4.750   0.1430   0.01467   0.00744  -0.1582   0.8059   0.2032
  -4.500   0.1706   0.01451   0.00728  -0.1583   0.8000   0.2230
  -4.250   0.1979   0.01438   0.00713  -0.1583   0.7935   0.2436
  -4.000   0.2280   0.01424   0.00692  -0.1587   0.7888   0.2652
  -3.750   0.2545   0.01417   0.00689  -0.1587   0.7829   0.2851
  -3.500   0.2823   0.01410   0.00681  -0.1587   0.7772   0.3059
  -3.250   0.3125   0.01403   0.00665  -0.1592   0.7728   0.3277
  -3.000   0.3389   0.01401   0.00667  -0.1590   0.7670   0.3474
  -2.750   0.3665   0.01396   0.00665  -0.1590   0.7616   0.3673
  -2.500   0.3963   0.01392   0.00656  -0.1594   0.7574   0.3884
  -2.250   0.4234   0.01394   0.00660  -0.1593   0.7522   0.4090
  -2.000   0.4504   0.01394   0.00662  -0.1592   0.7468   0.4294
  -1.750   0.4795   0.01390   0.00660  -0.1595   0.7426   0.4503
  -1.500   0.5082   0.01393   0.00662  -0.1596   0.7384   0.4719
  -1.250   0.5340   0.01399   0.00672  -0.1594   0.7327   0.4941
  -1.000   0.5621   0.01397   0.00676  -0.1594   0.7283   0.5160
  -0.750   0.5922   0.01398   0.00675  -0.1598   0.7247   0.5406
  -0.500   0.6172   0.01406   0.00695  -0.1593   0.7193   0.5641
  -0.250   0.6440   0.01410   0.00705  -0.1591   0.7145   0.5898
   0.000   0.6727   0.01411   0.00709  -0.1592   0.7107   0.6166
   0.250   0.7002   0.01418   0.00722  -0.1591   0.7066   0.6450
   0.500   0.7245   0.01428   0.00744  -0.1584   0.7012   0.6744
   0.750   0.7509   0.01430   0.00755  -0.1580   0.6970   0.7049
   1.000   0.7788   0.01432   0.00760  -0.1578   0.6935   0.7377
   1.250   0.8008   0.01444   0.00786  -0.1566   0.6885   0.7716
   1.500   0.8223   0.01449   0.00804  -0.1552   0.6836   0.8078
   1.750   0.8440   0.01446   0.00808  -0.1535   0.6798   0.8501
   2.000   0.8637   0.01438   0.00804  -0.1513   0.6764   0.9048
   2.250   0.8900   0.01445   0.00821  -0.1513   0.6706   1.0000
   2.500   0.9208   0.01462   0.00832  -0.1522   0.6660   1.0000
   2.750   0.9534   0.01475   0.00835  -0.1533   0.6624   1.0000
   3.000   0.9799   0.01503   0.00865  -0.1534   0.6574   1.0000
   3.250   1.0068   0.01525   0.00888  -0.1534   0.6521   1.0000
   3.500   1.0371   0.01538   0.00895  -0.1540   0.6480   1.0000
   3.750   1.0663   0.01559   0.00914  -0.1544   0.6437   1.0000
   4.000   1.0901   0.01586   0.00948  -0.1539   0.6376   1.0000
   4.250   1.1194   0.01598   0.00957  -0.1542   0.6329   1.0000
   4.500   1.1497   0.01613   0.00969  -0.1547   0.6286   1.0000
   4.750   1.1718   0.01641   0.01008  -0.1539   0.6219   1.0000
   5.000   1.2010   0.01649   0.01014  -0.1541   0.6168   1.0000
   5.250   1.2284   0.01668   0.01034  -0.1541   0.6114   1.0000
   5.500   1.2520   0.01686   0.01060  -0.1534   0.6044   1.0000
   5.750   1.2835   0.01686   0.01055  -0.1540   0.5992   1.0000
   6.000   1.3043   0.01712   0.01093  -0.1529   0.5916   1.0000
   6.250   1.3325   0.01715   0.01097  -0.1529   0.5853   1.0000
   6.500   1.3563   0.01733   0.01121  -0.1522   0.5780   1.0000
   6.750   1.3818   0.01736   0.01128  -0.1517   0.5703   1.0000
   7.000   1.4049   0.01749   0.01148  -0.1508   0.5621   1.0000
   7.250   1.4303   0.01750   0.01151  -0.1503   0.5538   1.0000
   7.500   1.4504   0.01767   0.01178  -0.1489   0.5446   1.0000
   7.750   1.4773   0.01764   0.01173  -0.1486   0.5359   1.0000
   8.000   1.4932   0.01783   0.01206  -0.1465   0.5248   1.0000
   8.250   1.5119   0.01797   0.01228  -0.1448   0.5139   1.0000
   8.500   1.5309   0.01810   0.01244  -0.1432   0.5023   1.0000
   8.750   1.5478   0.01826   0.01263  -0.1411   0.4894   1.0000
   9.000   1.5602   0.01853   0.01296  -0.1384   0.4750   1.0000
   9.250   1.5693   0.01885   0.01331  -0.1351   0.4593   1.0000
   9.500   1.5745   0.01930   0.01380  -0.1312   0.4426   1.0000
   9.750   1.5781   0.01989   0.01441  -0.1273   0.4241   1.0000
  10.000   1.5802   0.02064   0.01515  -0.1233   0.4038   1.0000
  10.250   1.5803   0.02162   0.01607  -0.1193   0.3824   1.0000
  10.500   1.5785   0.02284   0.01724  -0.1154   0.3586   1.0000
  10.750   1.5739   0.02436   0.01867  -0.1115   0.3347   1.0000
  11.000   1.5682   0.02614   0.02037  -0.1078   0.3102   1.0000
  11.250   1.5617   0.02818   0.02233  -0.1044   0.2864   1.0000
  11.500   1.5537   0.03052   0.02457  -0.1013   0.2635   1.0000
  11.750   1.5464   0.03301   0.02700  -0.0986   0.2410   1.0000
  12.000   1.5383   0.03575   0.02965  -0.0962   0.2199   1.0000
  12.250   1.5305   0.03864   0.03247  -0.0941   0.2000   1.0000
  12.500   1.5238   0.04160   0.03538  -0.0923   0.1805   1.0000
  12.750   1.5163   0.04480   0.03852  -0.0907   0.1625   1.0000
  13.000   1.5087   0.04816   0.04182  -0.0894   0.1460   1.0000
  13.250   1.5023   0.05156   0.04517  -0.0883   0.1303   1.0000
  13.500   1.4965   0.05503   0.04861  -0.0875   0.1157   1.0000
  13.750   1.4903   0.05866   0.05221  -0.0868   0.1026   1.0000
  14.000   1.4837   0.06247   0.05598  -0.0863   0.0911   1.0000
  14.250   1.4777   0.06634   0.05983  -0.0859   0.0809   1.0000
  14.500   1.4740   0.07003   0.06355  -0.0857   0.0717   1.0000
  14.750   1.4695   0.07390   0.06746  -0.0856   0.0642   1.0000
  15.000   1.4613   0.07835   0.07185  -0.0857   0.0584   1.0000
  15.250   1.4615   0.08180   0.07542  -0.0859   0.0525   1.0000
  15.500   1.4551   0.08614   0.07975  -0.0862   0.0482   1.0000
  15.750   1.4549   0.08976   0.08350  -0.0866   0.0439   1.0000
  16.000   1.4492   0.09408   0.08777  -0.0871   0.0405   1.0000
  16.250   1.4500   0.09768   0.09153  -0.0876   0.0371   1.0000
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