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EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 396 AIRFOIL (e396-il)
Reynolds number: 100,000
Max Cl/Cd: 57.7 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e396-il-100000-n5.txt
Download as CSV file: xf-e396-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 396 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2299   0.09581   0.09102  -0.0790   0.9622   0.0261
  -9.750  -0.2253   0.08959   0.08482  -0.0842   0.9574   0.0262
  -9.500  -0.2302   0.08265   0.07793  -0.0890   0.9487   0.0264
  -9.250  -0.2453   0.07258   0.06790  -0.0966   0.9406   0.0264
  -9.000  -0.2760   0.05867   0.05392  -0.1097   0.9300   0.0253
  -8.750  -0.3075   0.04534   0.04017  -0.1276   0.9115   0.0243
  -8.500  -0.3001   0.03910   0.03335  -0.1357   0.9031   0.0251
  -8.250  -0.2893   0.03536   0.02910  -0.1383   0.8942   0.0264
  -8.000  -0.2649   0.03222   0.02549  -0.1416   0.8895   0.0289
  -7.750  -0.2405   0.03091   0.02407  -0.1431   0.8840   0.0323
  -7.500  -0.2166   0.02889   0.02161  -0.1442   0.8780   0.0362
  -7.250  -0.1859   0.02744   0.02006  -0.1464   0.8745   0.0413
  -7.000  -0.1606   0.02616   0.01841  -0.1469   0.8689   0.0475
  -6.750  -0.1341   0.02520   0.01739  -0.1478   0.8636   0.0543
  -6.500  -0.1020   0.02403   0.01600  -0.1494   0.8603   0.0623
  -6.250  -0.0744   0.02329   0.01504  -0.1499   0.8553   0.0712
  -6.000  -0.0483   0.02263   0.01435  -0.1503   0.8498   0.0805
  -5.750  -0.0163   0.02187   0.01347  -0.1515   0.8463   0.0912
  -5.500   0.0145   0.02126   0.01273  -0.1525   0.8426   0.1040
  -5.250   0.0384   0.02087   0.01227  -0.1522   0.8364   0.1161
  -5.000   0.0697   0.02040   0.01172  -0.1532   0.8326   0.1318
  -4.750   0.1033   0.01993   0.01117  -0.1545   0.8297   0.1495
  -4.500   0.1255   0.01977   0.01098  -0.1538   0.8231   0.1657
  -4.250   0.1556   0.01948   0.01058  -0.1545   0.8189   0.1849
  -4.000   0.1883   0.01915   0.01023  -0.1556   0.8158   0.2051
  -3.750   0.2122   0.01907   0.01013  -0.1551   0.8099   0.2241
  -3.500   0.2406   0.01892   0.00992  -0.1554   0.8053   0.2452
  -3.250   0.2725   0.01869   0.00966  -0.1562   0.8020   0.2671
  -3.000   0.2985   0.01865   0.00958  -0.1560   0.7969   0.2882
  -2.750   0.3248   0.01859   0.00954  -0.1559   0.7918   0.3092
  -2.500   0.3558   0.01844   0.00934  -0.1565   0.7882   0.3329
  -2.250   0.3842   0.01836   0.00927  -0.1567   0.7841   0.3554
  -2.000   0.4079   0.01843   0.00935  -0.1561   0.7783   0.3779
  -1.750   0.4375   0.01833   0.00925  -0.1564   0.7744   0.4022
  -1.500   0.4695   0.01818   0.00910  -0.1571   0.7714   0.4288
  -1.250   0.4896   0.01838   0.00935  -0.1559   0.7647   0.4524
  -1.000   0.5184   0.01832   0.00932  -0.1560   0.7605   0.4799
  -0.750   0.5498   0.01820   0.00922  -0.1566   0.7575   0.5100
  -0.500   0.5700   0.01840   0.00952  -0.1553   0.7510   0.5373
  -0.250   0.5976   0.01839   0.00955  -0.1552   0.7465   0.5695
   0.000   0.6283   0.01829   0.00948  -0.1555   0.7433   0.6047
   0.250   0.6480   0.01849   0.00981  -0.1541   0.7369   0.6380
   0.500   0.6735   0.01850   0.00989  -0.1535   0.7322   0.6762
   0.750   0.7018   0.01838   0.00984  -0.1532   0.7289   0.7184
   1.000   0.7178   0.01858   0.01018  -0.1509   0.7223   0.7617
   1.250   0.7383   0.01853   0.01023  -0.1490   0.7175   0.8149
   1.500   0.7617   0.01826   0.01005  -0.1474   0.7141   0.8950
   1.750   0.7837   0.01854   0.01035  -0.1468   0.7069   1.0000
   2.000   0.8142   0.01866   0.01040  -0.1474   0.7024   1.0000
   2.250   0.8486   0.01866   0.01032  -0.1486   0.6991   1.0000
   2.500   0.8666   0.01916   0.01084  -0.1473   0.6914   1.0000
   2.750   0.8976   0.01923   0.01086  -0.1479   0.6870   1.0000
   3.000   0.9235   0.01948   0.01110  -0.1477   0.6816   1.0000
   3.250   0.9473   0.01978   0.01142  -0.1472   0.6752   1.0000
   3.500   0.9799   0.01979   0.01139  -0.1480   0.6712   1.0000
   3.750   0.9987   0.02024   0.01190  -0.1467   0.6636   1.0000
   4.000   1.0278   0.02034   0.01201  -0.1470   0.6584   1.0000
   4.250   1.0521   0.02059   0.01231  -0.1464   0.6521   1.0000
   4.500   1.0763   0.02083   0.01258  -0.1459   0.6453   1.0000
   4.750   1.1060   0.02088   0.01265  -0.1461   0.6399   1.0000
   5.000   1.1249   0.02127   0.01314  -0.1448   0.6316   1.0000
   5.250   1.1551   0.02127   0.01316  -0.1450   0.6257   1.0000
   5.500   1.1732   0.02164   0.01362  -0.1435   0.6167   1.0000
   5.750   1.1979   0.02178   0.01382  -0.1429   0.6089   1.0000
   6.000   1.2220   0.02192   0.01404  -0.1421   0.6004   1.0000
   6.250   1.2403   0.02225   0.01446  -0.1406   0.5909   1.0000
   6.500   1.2682   0.02224   0.01450  -0.1404   0.5825   1.0000
   6.750   1.2861   0.02254   0.01489  -0.1387   0.5718   1.0000
   7.000   1.3030   0.02287   0.01534  -0.1369   0.5606   1.0000
   7.250   1.3220   0.02310   0.01565  -0.1353   0.5495   1.0000
   7.500   1.3416   0.02330   0.01591  -0.1337   0.5378   1.0000
   7.750   1.3595   0.02356   0.01623  -0.1320   0.5250   1.0000
   8.000   1.3744   0.02393   0.01665  -0.1298   0.5109   1.0000
   8.250   1.3867   0.02441   0.01720  -0.1273   0.4956   1.0000
   8.500   1.3978   0.02499   0.01787  -0.1247   0.4795   1.0000
   8.750   1.4077   0.02565   0.01859  -0.1221   0.4621   1.0000
   9.000   1.4174   0.02638   0.01934  -0.1195   0.4434   1.0000
   9.250   1.4258   0.02721   0.02017  -0.1168   0.4230   1.0000
   9.500   1.4311   0.02827   0.02123  -0.1140   0.4007   1.0000
   9.750   1.4355   0.02947   0.02240  -0.1112   0.3771   1.0000
  10.000   1.4382   0.03086   0.02372  -0.1084   0.3525   1.0000
  10.250   1.4391   0.03249   0.02530  -0.1057   0.3269   1.0000
  10.500   1.4388   0.03432   0.02709  -0.1030   0.3015   1.0000
  10.750   1.4374   0.03635   0.02903  -0.1006   0.2769   1.0000
  11.000   1.4351   0.03857   0.03118  -0.0982   0.2533   1.0000
  11.250   1.4331   0.04091   0.03346  -0.0962   0.2305   1.0000
  11.750   1.4280   0.04602   0.03847  -0.0926   0.1890   1.0000
  12.000   1.4249   0.04881   0.04121  -0.0911   0.1701   1.0000
  12.250   1.4221   0.05168   0.04405  -0.0898   0.1525   1.0000
  12.500   1.4202   0.05460   0.04696  -0.0887   0.1359   1.0000
  12.750   1.4178   0.05767   0.05002  -0.0877   0.1206   1.0000
  13.000   1.4155   0.06084   0.05319  -0.0870   0.1071   1.0000
  13.250   1.4132   0.06412   0.05650  -0.0863   0.0952   1.0000
  13.500   1.4103   0.06757   0.06000  -0.0859   0.0844   1.0000
  13.750   1.4064   0.07126   0.06368  -0.0856   0.0755   1.0000
  14.000   1.4045   0.07480   0.06731  -0.0854   0.0670   1.0000
  14.250   1.4017   0.07853   0.07112  -0.0854   0.0600   1.0000
  14.500   1.3971   0.08263   0.07525  -0.0856   0.0541   1.0000
  14.750   1.3949   0.08646   0.07919  -0.0858   0.0489   1.0000
  15.000   1.3908   0.09067   0.08349  -0.0863   0.0445   1.0000
  15.250   1.3862   0.09500   0.08789  -0.0870   0.0409   1.0000
  15.500   1.3844   0.09899   0.09204  -0.0876   0.0373   1.0000
  15.750   1.3799   0.10347   0.09662  -0.0886   0.0346   1.0000
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