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EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 399 AIRFOIL (e399-il)
Reynolds number: 200,000
Max Cl/Cd: 83.55 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e399-il-200000.txt
Download as CSV file: xf-e399-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 399 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5136   0.06721   0.06358  -0.0851   0.9926   0.0223
 -11.250  -0.5218   0.05831   0.05447  -0.0967   0.9851   0.0221
 -11.000  -0.5267   0.05060   0.04647  -0.1081   0.9752   0.0220
 -10.750  -0.5303   0.04433   0.03986  -0.1180   0.9625   0.0220
 -10.500  -0.5265   0.03866   0.03361  -0.1272   0.9492   0.0223
 -10.250  -0.5000   0.03552   0.03040  -0.1314   0.9449   0.0232
 -10.000  -0.4786   0.03336   0.02807  -0.1339   0.9367   0.0244
  -9.750  -0.4500   0.03058   0.02473  -0.1383   0.9316   0.0263
  -9.500  -0.4137   0.02871   0.02291  -0.1421   0.9293   0.0289
  -9.250  -0.3916   0.02668   0.02056  -0.1430   0.9208   0.0313
  -9.000  -0.3578   0.02503   0.01887  -0.1456   0.9164   0.0344
  -8.750  -0.3208   0.02342   0.01715  -0.1489   0.9132   0.0399
  -8.500  -0.2980   0.02239   0.01605  -0.1491   0.9038   0.0453
  -8.250  -0.2636   0.02120   0.01477  -0.1514   0.8991   0.0532
  -8.000  -0.2358   0.02034   0.01383  -0.1523   0.8917   0.0613
  -7.750  -0.2060   0.01952   0.01294  -0.1534   0.8847   0.0703
  -7.500  -0.1729   0.01870   0.01203  -0.1551   0.8794   0.0804
  -7.250  -0.1491   0.01809   0.01136  -0.1548   0.8703   0.0898
  -7.000  -0.1170   0.01742   0.01060  -0.1560   0.8649   0.1016
  -6.750  -0.0923   0.01701   0.01012  -0.1558   0.8565   0.1132
  -6.500  -0.0625   0.01648   0.00953  -0.1565   0.8502   0.1272
  -6.250  -0.0351   0.01606   0.00907  -0.1568   0.8433   0.1421
  -6.000  -0.0078   0.01566   0.00867  -0.1569   0.8361   0.1581
  -5.750   0.0232   0.01528   0.00825  -0.1578   0.8311   0.1762
  -5.500   0.0480   0.01507   0.00805  -0.1575   0.8233   0.1936
  -5.250   0.0774   0.01482   0.00776  -0.1580   0.8174   0.2132
  -5.000   0.1064   0.01465   0.00752  -0.1583   0.8117   0.2334
  -4.750   0.1328   0.01453   0.00738  -0.1582   0.8047   0.2527
  -4.500   0.1627   0.01437   0.00722  -0.1587   0.7997   0.2725
  -4.250   0.1905   0.01431   0.00714  -0.1588   0.7940   0.2917
  -4.000   0.2176   0.01426   0.00708  -0.1588   0.7876   0.3104
  -3.750   0.2477   0.01419   0.00694  -0.1592   0.7828   0.3296
  -3.500   0.2753   0.01419   0.00692  -0.1592   0.7774   0.3474
  -3.250   0.3022   0.01417   0.00691  -0.1591   0.7715   0.3645
  -3.000   0.3319   0.01412   0.00681  -0.1595   0.7668   0.3821
  -2.750   0.3604   0.01413   0.00679  -0.1596   0.7620   0.3987
  -2.500   0.3866   0.01415   0.00684  -0.1594   0.7562   0.4147
  -2.250   0.4155   0.01413   0.00680  -0.1596   0.7515   0.4312
  -2.000   0.4462   0.01413   0.00674  -0.1601   0.7477   0.4479
  -1.750   0.4710   0.01419   0.00687  -0.1597   0.7418   0.4637
  -1.500   0.4987   0.01421   0.00689  -0.1597   0.7370   0.4802
  -1.250   0.5285   0.01421   0.00687  -0.1600   0.7330   0.4975
  -1.000   0.5562   0.01428   0.00696  -0.1600   0.7285   0.5145
  -0.750   0.5820   0.01435   0.00709  -0.1598   0.7231   0.5317
  -0.500   0.6103   0.01437   0.00713  -0.1598   0.7188   0.5499
  -0.250   0.6406   0.01439   0.00714  -0.1602   0.7153   0.5690
   0.000   0.6656   0.01452   0.00736  -0.1598   0.7101   0.5880
   0.250   0.6920   0.01460   0.00750  -0.1596   0.7053   0.6081
   0.500   0.7207   0.01464   0.00755  -0.1597   0.7013   0.6302
   0.750   0.7508   0.01468   0.00761  -0.1600   0.6980   0.6516
   1.000   0.7731   0.01484   0.00792  -0.1591   0.6924   0.6734
   1.250   0.7993   0.01492   0.00807  -0.1588   0.6878   0.6978
   1.500   0.8271   0.01494   0.00815  -0.1586   0.6840   0.7220
   1.750   0.8541   0.01505   0.00830  -0.1583   0.6802   0.7486
   2.000   0.8746   0.01519   0.00861  -0.1569   0.6747   0.7745
   2.250   0.8985   0.01524   0.00873  -0.1559   0.6703   0.8036
   2.500   0.9233   0.01523   0.00877  -0.1550   0.6667   0.8357
   2.750   0.9409   0.01531   0.00897  -0.1527   0.6622   0.8729
   3.000   0.9547   0.01528   0.00907  -0.1496   0.6568   0.9311
   3.250   0.9898   0.01530   0.00907  -0.1513   0.6525   1.0000
   3.500   1.0253   0.01543   0.00910  -0.1530   0.6489   1.0000
   3.750   1.0489   0.01577   0.00951  -0.1527   0.6428   1.0000
   4.000   1.0775   0.01594   0.00968  -0.1531   0.6377   1.0000
   4.250   1.1099   0.01604   0.00971  -0.1540   0.6337   1.0000
   4.500   1.1347   0.01633   0.01006  -0.1537   0.6280   1.0000
   4.750   1.1608   0.01652   0.01028  -0.1536   0.6222   1.0000
   5.000   1.1924   0.01658   0.01030  -0.1543   0.6176   1.0000
   5.250   1.2165   0.01685   0.01063  -0.1538   0.6114   1.0000
   5.500   1.2423   0.01698   0.01080  -0.1535   0.6050   1.0000
   5.750   1.2753   0.01699   0.01074  -0.1543   0.6000   1.0000
   6.000   1.2946   0.01726   0.01115  -0.1529   0.5922   1.0000
   6.250   1.3235   0.01728   0.01116  -0.1531   0.5859   1.0000
   6.500   1.3474   0.01746   0.01140  -0.1524   0.5788   1.0000
   6.750   1.3723   0.01752   0.01152  -0.1519   0.5712   1.0000
   7.000   1.3978   0.01762   0.01164  -0.1514   0.5638   1.0000
   7.250   1.4203   0.01770   0.01179  -0.1504   0.5551   1.0000
   7.500   1.4432   0.01780   0.01195  -0.1495   0.5466   1.0000
   7.750   1.4662   0.01783   0.01202  -0.1486   0.5372   1.0000
   8.000   1.4841   0.01800   0.01228  -0.1468   0.5269   1.0000
   8.250   1.5062   0.01806   0.01236  -0.1456   0.5168   1.0000
   8.500   1.5223   0.01822   0.01259  -0.1435   0.5051   1.0000
   8.750   1.5359   0.01845   0.01291  -0.1410   0.4924   1.0000
   9.000   1.5490   0.01869   0.01321  -0.1384   0.4791   1.0000
   9.250   1.5584   0.01898   0.01353  -0.1351   0.4649   1.0000
   9.500   1.5652   0.01939   0.01396  -0.1315   0.4494   1.0000
   9.750   1.5701   0.01993   0.01451  -0.1277   0.4324   1.0000
  10.000   1.5731   0.02063   0.01519  -0.1239   0.4136   1.0000
  10.250   1.5740   0.02154   0.01604  -0.1200   0.3933   1.0000
  10.500   1.5729   0.02267   0.01715  -0.1161   0.3711   1.0000
  10.750   1.5693   0.02409   0.01850  -0.1122   0.3480   1.0000
  11.000   1.5646   0.02576   0.02009  -0.1085   0.3244   1.0000
  11.250   1.5578   0.02774   0.02198  -0.1050   0.3008   1.0000
  11.500   1.5509   0.02993   0.02409  -0.1019   0.2777   1.0000
  11.750   1.5431   0.03239   0.02647  -0.0991   0.2554   1.0000
  12.000   1.5350   0.03505   0.02905  -0.0965   0.2346   1.0000
  12.250   1.5279   0.03782   0.03176  -0.0944   0.2137   1.0000
  12.500   1.5202   0.04080   0.03467  -0.0924   0.1946   1.0000
  12.750   1.5122   0.04398   0.03778  -0.0908   0.1769   1.0000
  13.000   1.5060   0.04715   0.04092  -0.0894   0.1595   1.0000
  13.250   1.5000   0.05045   0.04418  -0.0883   0.1430   1.0000
  13.500   1.4940   0.05389   0.04757  -0.0874   0.1279   1.0000
  13.750   1.4882   0.05744   0.05109  -0.0866   0.1142   1.0000
  14.000   1.4824   0.06109   0.05472  -0.0861   0.1019   1.0000
  14.250   1.4767   0.06488   0.05848  -0.0857   0.0910   1.0000
  14.500   1.4701   0.06886   0.06243  -0.0854   0.0817   1.0000
  14.750   1.4650   0.07280   0.06636  -0.0854   0.0731   1.0000
  15.000   1.4618   0.07658   0.07019  -0.0854   0.0654   1.0000
  15.250   1.4569   0.08065   0.07428  -0.0856   0.0593   1.0000
  15.500   1.4519   0.08482   0.07845  -0.0859   0.0542   1.0000
  15.750   1.4505   0.08856   0.08228  -0.0862   0.0492   1.0000
  16.000   1.4448   0.09289   0.08657  -0.0868   0.0456   1.0000
  16.250   1.4454   0.09651   0.09033  -0.0873   0.0417   1.0000
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