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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 100,000
Max Cl/Cd: 67.24 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e385-il-100000.txt
Download as CSV file: xf-e385-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2874   0.10699   0.10271  -0.0287   1.0000   0.0584
  -7.500  -0.3027   0.10672   0.10256  -0.0254   1.0000   0.0596
  -7.250  -0.3182   0.10648   0.10242  -0.0222   1.0000   0.0597
  -7.000  -0.3273   0.10572   0.10174  -0.0215   0.9984   0.0612
  -6.750  -0.3097   0.10407   0.10010  -0.0330   0.9870   0.0636
  -6.500  -0.2711   0.10085   0.09687  -0.0538   0.9737   0.0644
  -6.250  -0.2639   0.09403   0.09005  -0.0435   0.9734   0.0663
  -6.000  -0.2438   0.09009   0.08611  -0.0451   0.9664   0.0695
  -5.750  -0.2144   0.08597   0.08193  -0.0528   0.9591   0.0738
  -5.500  -0.1607   0.08201   0.07783  -0.0803   0.9454   0.0785
  -5.250  -0.1614   0.07770   0.07361  -0.0719   0.9390   0.0801
  -5.000  -0.1395   0.07413   0.07003  -0.0724   0.9334   0.0838
  -4.500  -0.0692   0.06539   0.06114  -0.0909   0.9186   0.0955
  -4.250  -0.0486   0.06261   0.05832  -0.0925   0.9106   0.1012
  -4.000  -0.0015   0.05768   0.05325  -0.1037   0.9050   0.1108
  -3.750   0.0429   0.05360   0.04897  -0.1130   0.8989   0.1240
  -3.500   0.0798   0.05021   0.04545  -0.1185   0.8924   0.1389
  -3.250   0.1193   0.04694   0.04214  -0.1225   0.8894   0.1570
  -3.000   0.1527   0.04447   0.03948  -0.1272   0.8810   0.1837
  -2.750   0.1934   0.04155   0.03650  -0.1310   0.8771   0.2074
  -2.500   0.3108   0.02976   0.02270  -0.1510   0.8777   0.0724
  -2.250   0.3661   0.02678   0.01873  -0.1553   0.8754   0.0646
  -2.000   0.3994   0.02496   0.01663  -0.1565   0.8688   0.0660
  -1.750   0.4371   0.02374   0.01525  -0.1582   0.8635   0.0746
  -1.500   0.4801   0.02211   0.01352  -0.1604   0.8603   0.0855
  -1.250   0.5070   0.02134   0.01288  -0.1603   0.8522   0.1247
  -1.000   0.5470   0.01919   0.01225  -0.1630   0.8482   0.4973
  -0.750   0.5571   0.01825   0.01212  -0.1579   0.8414   1.0000
  -0.500   0.5882   0.01845   0.01193  -0.1585   0.8345   1.0000
  -0.250   0.6263   0.01836   0.01152  -0.1600   0.8306   1.0000
   0.000   0.6483   0.01892   0.01189  -0.1593   0.8212   1.0000
   0.250   0.6840   0.01889   0.01163  -0.1604   0.8168   1.0000
   0.500   0.7063   0.01947   0.01209  -0.1598   0.8081   1.0000
   0.750   0.7399   0.01951   0.01196  -0.1606   0.8032   1.0000
   1.000   0.7632   0.02006   0.01243  -0.1602   0.7951   1.0000
   1.250   0.7945   0.02021   0.01246  -0.1606   0.7896   1.0000
   1.500   0.8198   0.02067   0.01286  -0.1604   0.7825   1.0000
   1.750   0.8481   0.02097   0.01310  -0.1605   0.7760   1.0000
   2.000   0.8784   0.02116   0.01324  -0.1607   0.7707   1.0000
   2.250   0.9008   0.02178   0.01384  -0.1601   0.7624   1.0000
   2.500   0.9347   0.02175   0.01376  -0.1607   0.7582   1.0000
   2.750   0.9531   0.02262   0.01466  -0.1597   0.7486   1.0000
   3.000   0.9866   0.02256   0.01461  -0.1602   0.7441   1.0000
   3.250   1.0053   0.02342   0.01551  -0.1592   0.7345   1.0000
   3.500   1.0391   0.02330   0.01538  -0.1596   0.7296   1.0000
   3.750   1.0581   0.02410   0.01626  -0.1585   0.7198   1.0000
   4.000   1.0928   0.02385   0.01606  -0.1589   0.7147   1.0000
   4.250   1.1119   0.02460   0.01690  -0.1578   0.7044   1.0000
   4.500   1.1424   0.02458   0.01693  -0.1577   0.6976   1.0000
   4.750   1.1673   0.02487   0.01731  -0.1570   0.6883   1.0000
   5.000   1.1911   0.02522   0.01780  -0.1561   0.6786   1.0000
   5.250   1.2258   0.02473   0.01736  -0.1562   0.6713   1.0000
   5.500   1.2479   0.02507   0.01783  -0.1550   0.6597   1.0000
   5.750   1.2734   0.02514   0.01805  -0.1541   0.6489   1.0000
   6.000   1.3041   0.02480   0.01780  -0.1537   0.6390   1.0000
   6.250   1.3342   0.02440   0.01750  -0.1531   0.6276   1.0000
   6.500   1.3595   0.02423   0.01748  -0.1519   0.6139   1.0000
   6.750   1.3859   0.02392   0.01733  -0.1508   0.5994   1.0000
   7.000   1.4129   0.02351   0.01703  -0.1497   0.5839   1.0000
   7.250   1.4340   0.02336   0.01708  -0.1478   0.5652   1.0000
   7.500   1.4571   0.02291   0.01676  -0.1460   0.5434   1.0000
   7.750   1.4767   0.02228   0.01619  -0.1433   0.5119   1.0000
   8.000   1.4886   0.02214   0.01606  -0.1398   0.4683   1.0000
   8.250   1.4957   0.02256   0.01634  -0.1359   0.4108   1.0000
   8.500   1.4975   0.02368   0.01709  -0.1316   0.3415   1.0000
   8.750   1.4931   0.02546   0.01844  -0.1269   0.2756   1.0000
   9.000   1.4820   0.02761   0.02019  -0.1215   0.2176   1.0000
   9.250   1.4661   0.03032   0.02246  -0.1162   0.1603   1.0000
   9.500   1.4464   0.03379   0.02543  -0.1112   0.1083   1.0000
   9.750   1.4287   0.03756   0.02884  -0.1071   0.0789   1.0000
  10.000   1.4194   0.04091   0.03212  -0.1040   0.0645   1.0000
  10.250   1.4126   0.04418   0.03538  -0.1015   0.0577   1.0000
  10.500   1.4148   0.04685   0.03818  -0.0994   0.0525   1.0000
  10.750   1.4190   0.04947   0.04080  -0.0976   0.0487   1.0000
  11.000   1.4354   0.05187   0.04315  -0.0956   0.0455   1.0000
  11.250   1.4561   0.05389   0.04536  -0.0941   0.0426   1.0000
  11.500   1.4728   0.05615   0.04776  -0.0930   0.0397   1.0000
  11.750   1.5075   0.05895   0.05060  -0.0925   0.0374   1.0000
  12.000   1.5550   0.06474   0.05677  -0.0935   0.0365   1.0000
  12.250   1.5629   0.06920   0.06160  -0.0921   0.0364   1.0000
  12.500   1.5612   0.07309   0.06587  -0.0901   0.0366   1.0000
  12.750   1.5540   0.07671   0.06984  -0.0881   0.0368   1.0000
  13.000   1.5425   0.08054   0.07402  -0.0864   0.0370   1.0000
  13.250   1.5272   0.08463   0.07847  -0.0850   0.0374   1.0000
  13.500   1.5080   0.08947   0.08370  -0.0843   0.0379   1.0000
  13.750   1.4835   0.09522   0.08985  -0.0845   0.0385   1.0000
  14.000   1.4535   0.10187   0.09687  -0.0859   0.0390   1.0000
  14.250   1.4243   0.10917   0.10451  -0.0885   0.0396   1.0000
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