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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 200,000
Max Cl/Cd: 96.79 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e385-il-200000-n5.txt
Download as CSV file: xf-e385-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E385  (8.41%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2598   0.11630   0.11276  -0.0384   1.0000   0.0172
  -9.500  -0.2581   0.11400   0.11051  -0.0381   1.0000   0.0176
  -9.250  -0.2575   0.11185   0.10840  -0.0375   1.0000   0.0178
  -9.000  -0.2447   0.10840   0.10496  -0.0405   0.9975   0.0184
  -8.750  -0.2284   0.10452   0.10108  -0.0446   0.9930   0.0192
  -8.500  -0.2120   0.10076   0.09733  -0.0499   0.9872   0.0204
  -8.250  -0.1972   0.09730   0.09388  -0.0551   0.9800   0.0207
  -8.000  -0.1820   0.09368   0.09027  -0.0614   0.9716   0.0208
  -7.500  -0.1522   0.08601   0.08262  -0.0653   0.9544   0.0218
  -7.250  -0.1327   0.08282   0.07941  -0.0682   0.9464   0.0236
  -7.000  -0.1148   0.07935   0.07594  -0.0726   0.9347   0.0243
  -6.750  -0.0948   0.07559   0.07215  -0.0789   0.9212   0.0261
  -6.500  -0.0639   0.07096   0.06747  -0.0919   0.9059   0.0270
  -6.250  -0.0342   0.06624   0.06268  -0.1015   0.8923   0.0272
  -6.000  -0.0102   0.06138   0.05777  -0.1079   0.8794   0.0274
  -5.750   0.0059   0.05811   0.05446  -0.1087   0.8677   0.0281
  -5.500   0.0275   0.05496   0.05124  -0.1120   0.8553   0.0287
  -5.250   0.0516   0.05151   0.04769  -0.1167   0.8430   0.0294
  -5.000   0.0789   0.04760   0.04365  -0.1224   0.8309   0.0297
  -4.500   0.1556   0.03244   0.02779  -0.1404   0.8100   0.0152
  -4.000   0.2246   0.02388   0.01831  -0.1487   0.7924   0.0142
  -3.750   0.2602   0.02031   0.01408  -0.1515   0.7847   0.0140
  -3.500   0.2933   0.01792   0.01109  -0.1530   0.7765   0.0143
  -3.250   0.3246   0.01652   0.00917  -0.1538   0.7689   0.0158
  -3.000   0.3541   0.01536   0.00777  -0.1544   0.7611   0.0167
  -2.750   0.3836   0.01443   0.00663  -0.1547   0.7539   0.0172
  -2.500   0.4128   0.01372   0.00576  -0.1549   0.7465   0.0178
  -2.250   0.4420   0.01316   0.00507  -0.1552   0.7397   0.0188
  -2.000   0.4712   0.01274   0.00449  -0.1555   0.7327   0.0202
  -1.750   0.5004   0.01240   0.00406  -0.1558   0.7265   0.0235
  -1.500   0.5294   0.01213   0.00375  -0.1560   0.7195   0.0316
  -1.250   0.5590   0.01179   0.00345  -0.1564   0.7138   0.0719
  -1.000   0.5880   0.01143   0.00340  -0.1570   0.7072   0.1668
  -0.750   0.6170   0.01107   0.00340  -0.1576   0.7012   0.3074
  -0.500   0.6453   0.01081   0.00343  -0.1579   0.6953   0.4364
  -0.250   0.6718   0.01044   0.00352  -0.1577   0.6893   0.6184
   0.250   0.7128   0.00989   0.00341  -0.1536   0.6780   1.0000
   0.500   0.7411   0.01002   0.00340  -0.1538   0.6725   1.0000
   0.750   0.7694   0.01015   0.00342  -0.1538   0.6672   1.0000
   1.000   0.7974   0.01027   0.00347  -0.1539   0.6612   1.0000
   1.250   0.8255   0.01042   0.00350  -0.1540   0.6562   1.0000
   1.500   0.8534   0.01056   0.00359  -0.1540   0.6504   1.0000
   1.750   0.8812   0.01070   0.00369  -0.1540   0.6447   1.0000
   2.000   0.9091   0.01086   0.00377  -0.1541   0.6399   1.0000
   2.250   0.9365   0.01100   0.00392  -0.1541   0.6336   1.0000
   2.500   0.9641   0.01116   0.00405  -0.1540   0.6281   1.0000
   2.750   0.9915   0.01132   0.00420  -0.1540   0.6223   1.0000
   3.000   1.0187   0.01148   0.00436  -0.1539   0.6158   1.0000
   3.250   1.0459   0.01164   0.00450  -0.1538   0.6095   1.0000
   3.500   1.0726   0.01179   0.00470  -0.1537   0.6014   1.0000
   3.750   1.0994   0.01196   0.00487  -0.1535   0.5939   1.0000
   4.000   1.1259   0.01212   0.00506  -0.1533   0.5855   1.0000
   4.250   1.1522   0.01229   0.00526  -0.1530   0.5768   1.0000
   4.500   1.1784   0.01247   0.00546  -0.1527   0.5677   1.0000
   4.750   1.2042   0.01264   0.00570  -0.1524   0.5570   1.0000
   5.000   1.2299   0.01283   0.00594  -0.1520   0.5466   1.0000
   5.250   1.2552   0.01304   0.00620  -0.1516   0.5356   1.0000
   5.500   1.2802   0.01325   0.00646  -0.1510   0.5227   1.0000
   5.750   1.3047   0.01348   0.00674  -0.1505   0.5078   1.0000
   6.000   1.3286   0.01374   0.00704  -0.1498   0.4903   1.0000
   6.250   1.3506   0.01408   0.00737  -0.1487   0.4627   1.0000
   6.500   1.3697   0.01459   0.00774  -0.1472   0.4207   1.0000
   6.750   1.3847   0.01543   0.00828  -0.1452   0.3615   1.0000
   7.000   1.3938   0.01676   0.00916  -0.1424   0.2874   1.0000
   7.250   1.4024   0.01821   0.01022  -0.1397   0.2236   1.0000
   7.500   1.4127   0.01951   0.01126  -0.1373   0.1747   1.0000
   7.750   1.4208   0.02094   0.01242  -0.1347   0.1283   1.0000
   8.000   1.4285   0.02230   0.01356  -0.1319   0.0917   1.0000
   8.250   1.4343   0.02360   0.01472  -0.1288   0.0636   1.0000
   8.500   1.4385   0.02501   0.01602  -0.1256   0.0402   1.0000
   8.750   1.4424   0.02651   0.01746  -0.1225   0.0254   1.0000
   9.000   1.4483   0.02794   0.01892  -0.1198   0.0192   1.0000
   9.250   1.4555   0.02933   0.02041  -0.1175   0.0166   1.0000
   9.750   1.4682   0.03246   0.02378  -0.1131   0.0139   1.0000
  10.000   1.4746   0.03412   0.02557  -0.1112   0.0129   1.0000
  10.250   1.4800   0.03594   0.02752  -0.1094   0.0122   1.0000
  10.500   1.4840   0.03799   0.02971  -0.1077   0.0117   1.0000
  10.750   1.4861   0.04030   0.03215  -0.1061   0.0113   1.0000
  11.000   1.4862   0.04292   0.03492  -0.1045   0.0110   1.0000
  11.250   1.4861   0.04567   0.03780  -0.1032   0.0108   1.0000
  11.500   1.4876   0.04834   0.04062  -0.1020   0.0106   1.0000
  11.750   1.4886   0.05115   0.04360  -0.1010   0.0105   1.0000
  12.000   1.4893   0.05408   0.04668  -0.1001   0.0103   1.0000
  12.250   1.4899   0.05709   0.04984  -0.0993   0.0102   1.0000
  12.500   1.4907   0.06017   0.05307  -0.0986   0.0100   1.0000
  12.750   1.4917   0.06330   0.05635  -0.0979   0.0099   1.0000
  13.000   1.4932   0.06646   0.05966  -0.0974   0.0097   1.0000
  13.250   1.4949   0.06966   0.06302  -0.0968   0.0096   1.0000
  13.500   1.4966   0.07294   0.06647  -0.0964   0.0095   1.0000
  13.750   1.4980   0.07633   0.07003  -0.0962   0.0093   1.0000
  14.000   1.4987   0.07989   0.07377  -0.0961   0.0090   1.0000
  14.250   1.4981   0.08366   0.07773  -0.0964   0.0087   1.0000
  14.500   1.4971   0.08760   0.08185  -0.0967   0.0086   1.0000
  14.750   1.4946   0.09179   0.08622  -0.0975   0.0084   1.0000
  15.000   1.4913   0.09622   0.09082  -0.0984   0.0082   1.0000
  15.250   1.4872   0.10090   0.09568  -0.0995   0.0081   1.0000
  15.500   1.4820   0.10586   0.10084  -0.1009   0.0080   1.0000
  15.750   1.4757   0.11113   0.10633  -0.1027   0.0080   1.0000
  16.000   1.4680   0.11682   0.11223  -0.1049   0.0079   1.0000
  16.250   1.4596   0.12278   0.11839  -0.1075   0.0079   1.0000
  16.500   1.4502   0.12918   0.12501  -0.1107   0.0078   1.0000
  16.750   1.4395   0.13597   0.13201  -0.1143   0.0078   1.0000
  17.000   1.4288   0.14316   0.13942  -0.1186   0.0078   1.0000
  17.250   1.4172   0.15080   0.14727  -0.1234   0.0078   1.0000
  17.500   1.4047   0.15907   0.15573  -0.1289   0.0078   1.0000
  17.750   1.3916   0.16798   0.16485  -0.1351   0.0078   1.0000
  18.000   1.3756   0.17856   0.17567  -0.1426   0.0079   1.0000
  18.250   1.3550   0.19169   0.18904  -0.1520   0.0081   1.0000
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