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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 100,000
Max Cl/Cd: 74.69 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e62-il-100000.txt
Download as CSV file: xf-e62-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E62  (5.62%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3524   0.10313   0.09862  -0.0203   1.0000   0.0518
  -6.750  -0.3597   0.10173   0.09730  -0.0183   1.0000   0.0529
  -6.500  -0.3679   0.10045   0.09610  -0.0163   1.0000   0.0543
  -6.250  -0.3723   0.09893   0.09465  -0.0159   1.0000   0.0557
  -6.000  -0.3749   0.09764   0.09343  -0.0172   1.0000   0.0570
  -5.750  -0.3713   0.09666   0.09251  -0.0227   1.0000   0.0579
  -5.500  -0.3556   0.09501   0.09085  -0.0319   1.0000   0.0584
  -5.250  -0.3605   0.08993   0.08586  -0.0266   1.0000   0.0594
  -5.000  -0.3623   0.08658   0.08255  -0.0215   1.0000   0.0608
  -4.750  -0.3579   0.08384   0.07983  -0.0205   1.0000   0.0628
  -4.500  -0.3488   0.08108   0.07708  -0.0220   1.0000   0.0654
  -4.250  -0.3312   0.07802   0.07398  -0.0269   1.0000   0.0692
  -4.000  -0.2818   0.07344   0.06926  -0.0439   1.0000   0.0729
  -3.750  -0.2830   0.07036   0.06625  -0.0394   1.0000   0.0745
  -3.500  -0.2709   0.06758   0.06347  -0.0393   1.0000   0.0777
  -3.250  -0.2069   0.06261   0.05823  -0.0567   1.0000   0.0871
  -3.000  -0.2019   0.05980   0.05551  -0.0537   1.0000   0.0896
  -2.750  -0.1459   0.05571   0.05115  -0.0660   1.0000   0.1014
  -2.500  -0.1346   0.05312   0.04863  -0.0645   1.0000   0.1051
  -2.250  -0.0809   0.04933   0.04464  -0.0738   0.9969   0.1194
  -2.000  -0.0152   0.04567   0.04065  -0.0855   0.9930   0.1446
  -1.750   0.0328   0.04303   0.03787  -0.0920   0.9886   0.1728
  -1.250   0.1876   0.03260   0.02555  -0.1128   0.9859   0.0852
  -1.000   0.2428   0.02926   0.02157  -0.1179   0.9845   0.0672
  -0.750   0.2882   0.02736   0.01900  -0.1209   0.9803   0.0613
  -0.500   0.3309   0.02628   0.01760  -0.1235   0.9761   0.0609
  -0.250   0.3748   0.02559   0.01683  -0.1266   0.9727   0.0678
   0.000   0.4105   0.02505   0.01628  -0.1285   0.9660   0.0831
   0.250   0.4490   0.02222   0.01578  -0.1302   0.9635   1.0000
   0.500   0.4857   0.02267   0.01580  -0.1323   0.9561   1.0000
   0.750   0.5243   0.02307   0.01591  -0.1347   0.9490   1.0000
   1.000   0.5570   0.02342   0.01606  -0.1361   0.9400   1.0000
   1.250   0.5977   0.02375   0.01622  -0.1388   0.9334   1.0000
   1.500   0.6313   0.02402   0.01638  -0.1403   0.9243   1.0000
   1.750   0.6644   0.02429   0.01659  -0.1416   0.9151   1.0000
   2.000   0.7088   0.02438   0.01662  -0.1447   0.9089   1.0000
   2.250   0.7397   0.02455   0.01678  -0.1455   0.8981   1.0000
   2.500   0.7740   0.02465   0.01690  -0.1467   0.8881   1.0000
   2.750   0.8214   0.02438   0.01670  -0.1500   0.8819   1.0000
   3.000   0.8537   0.02436   0.01674  -0.1506   0.8704   1.0000
   3.250   0.8895   0.02417   0.01664  -0.1517   0.8595   1.0000
   3.500   0.9336   0.02359   0.01618  -0.1539   0.8507   1.0000
   3.750   0.9810   0.02269   0.01550  -0.1563   0.8421   1.0000
   4.000   1.0219   0.02193   0.01492  -0.1576   0.8304   1.0000
   4.250   1.0679   0.02090   0.01410  -0.1594   0.8184   1.0000
   4.500   1.1136   0.01976   0.01319  -0.1610   0.8042   1.0000
   4.750   1.1601   0.01856   0.01230  -0.1625   0.7867   1.0000
   5.000   1.1942   0.01788   0.01183  -0.1620   0.7616   1.0000
   5.250   1.2268   0.01718   0.01127  -0.1609   0.7261   1.0000
   5.500   1.2494   0.01676   0.01084  -0.1577   0.6648   1.0000
   5.750   1.2645   0.01693   0.01064  -0.1535   0.5666   1.0000
   6.000   1.2695   0.01826   0.01101  -0.1484   0.4177   1.0000
   6.250   1.2686   0.02046   0.01217  -0.1433   0.2662   1.0000
   6.500   1.2588   0.02454   0.01457  -0.1375   0.0795   1.0000
   6.750   1.2656   0.02699   0.01684  -0.1336   0.0556   1.0000
   7.000   1.2771   0.02882   0.01882  -0.1305   0.0491   1.0000
   7.250   1.2896   0.03085   0.02086  -0.1278   0.0451   1.0000
   7.500   1.3119   0.03383   0.02387  -0.1267   0.0426   1.0000
   7.750   1.3416   0.03624   0.02650  -0.1264   0.0403   1.0000
   8.000   1.3688   0.03869   0.02917  -0.1260   0.0372   1.0000
   8.250   1.3985   0.04203   0.03282  -0.1258   0.0364   1.0000
   8.500   1.4227   0.04601   0.03733  -0.1245   0.0370   1.0000
   8.750   1.4391   0.05042   0.04235  -0.1222   0.0382   1.0000
   9.000   1.4495   0.05515   0.04762  -0.1194   0.0398   1.0000
   9.250   1.4556   0.06022   0.05313  -0.1166   0.0413   1.0000
   9.500   1.4690   0.06691   0.06008  -0.1154   0.0436   1.0000
   9.750   1.4445   0.07059   0.06482  -0.1075   0.0489   1.0000
  10.000   1.3391   0.06855   0.06340  -0.0910   0.0474   1.0000
  10.250   1.3107   0.07331   0.06849  -0.0863   0.0485   1.0000
  10.500   1.2810   0.07849   0.07394  -0.0827   0.0492   1.0000
  10.750   1.2507   0.08373   0.07943  -0.0804   0.0495   1.0000
  11.000   1.2184   0.08918   0.08510  -0.0793   0.0495   1.0000
  11.250   1.1825   0.09493   0.09107  -0.0794   0.0493   1.0000
  11.500   1.1427   0.10039   0.09673  -0.0806   0.0486   1.0000
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