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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 100,000
Max Cl/Cd: 74.44 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e62-il-100000-n5.txt
Download as CSV file: xf-e62-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3560   0.11444   0.10970  -0.0272   1.0000   0.0324
  -7.750  -0.3629   0.11335   0.10868  -0.0260   1.0000   0.0325
  -7.500  -0.3707   0.11227   0.10769  -0.0245   1.0000   0.0326
  -7.250  -0.3745   0.11066   0.10616  -0.0242   1.0000   0.0326
  -7.000  -0.3755   0.10872   0.10428  -0.0247   1.0000   0.0327
  -6.750  -0.3746   0.10495   0.10059  -0.0242   0.9997   0.0330
  -6.500  -0.3677   0.09925   0.09487  -0.0186   0.9995   0.0347
  -6.250  -0.3496   0.09552   0.09113  -0.0215   0.9958   0.0369
  -6.000  -0.3298   0.09182   0.08744  -0.0264   0.9908   0.0392
  -5.750  -0.3043   0.08786   0.08346  -0.0337   0.9854   0.0420
  -5.500  -0.2685   0.08424   0.07980  -0.0471   0.9774   0.0443
  -5.250  -0.2191   0.07968   0.07512  -0.0634   0.9722   0.0450
  -5.000  -0.2089   0.07462   0.07011  -0.0636   0.9667   0.0458
  -4.750  -0.1946   0.07080   0.06625  -0.0631   0.9629   0.0471
  -4.500  -0.1693   0.06709   0.06252  -0.0669   0.9588   0.0491
  -4.250  -0.1408   0.06334   0.05871  -0.0723   0.9528   0.0514
  -4.000  -0.0591   0.05749   0.05244  -0.0946   0.9495   0.0581
  -3.750  -0.0303   0.05259   0.04750  -0.0989   0.9455   0.0590
  -3.500  -0.0018   0.04882   0.04368  -0.1021   0.9407   0.0599
  -3.250   0.0509   0.04216   0.03669  -0.1103   0.9388   0.0300
  -3.000   0.1182   0.03509   0.02892  -0.1216   0.9383   0.0241
  -2.750   0.1646   0.03146   0.02491  -0.1275   0.9368   0.0232
  -2.500   0.2141   0.02810   0.02088  -0.1331   0.9358   0.0235
  -2.250   0.2544   0.02569   0.01786  -0.1362   0.9324   0.0249
  -2.000   0.2921   0.02381   0.01554  -0.1386   0.9290   0.0253
  -1.750   0.3305   0.02225   0.01362  -0.1408   0.9262   0.0255
  -1.500   0.3686   0.02103   0.01217  -0.1428   0.9239   0.0264
  -1.250   0.4024   0.02017   0.01115  -0.1441   0.9198   0.0278
  -1.000   0.4345   0.01953   0.01037  -0.1449   0.9146   0.0300
  -0.750   0.4711   0.01894   0.00970  -0.1467   0.9112   0.0379
  -0.500   0.5083   0.01828   0.00907  -0.1485   0.9079   0.0701
  -0.250   0.5408   0.01732   0.00913  -0.1503   0.9026   0.3992
   0.000   0.5628   0.01600   0.00889  -0.1483   0.8977   1.0000
   0.250   0.5937   0.01606   0.00871  -0.1489   0.8915   1.0000
   0.500   0.6261   0.01607   0.00853  -0.1497   0.8857   1.0000
   1.000   0.6903   0.01605   0.00824  -0.1512   0.8734   1.0000
   1.250   0.7278   0.01589   0.00800  -0.1528   0.8691   1.0000
   1.500   0.7561   0.01594   0.00800  -0.1528   0.8601   1.0000
   1.750   0.7946   0.01576   0.00780  -0.1547   0.8551   1.0000
   2.000   0.8233   0.01579   0.00783  -0.1547   0.8454   1.0000
   2.250   0.8582   0.01567   0.00772  -0.1558   0.8377   1.0000
   2.500   0.8921   0.01555   0.00766  -0.1566   0.8286   1.0000
   2.750   0.9226   0.01553   0.00768  -0.1569   0.8174   1.0000
   3.000   0.9548   0.01545   0.00766  -0.1574   0.8056   1.0000
   3.250   0.9871   0.01538   0.00766  -0.1578   0.7924   1.0000
   3.500   1.0187   0.01533   0.00774  -0.1581   0.7776   1.0000
   3.750   1.0502   0.01530   0.00779  -0.1584   0.7610   1.0000
   4.000   1.0812   0.01528   0.00785  -0.1585   0.7417   1.0000
   4.250   1.1090   0.01536   0.00801  -0.1580   0.7184   1.0000
   4.500   1.1360   0.01547   0.00826  -0.1574   0.6917   1.0000
   4.750   1.1624   0.01563   0.00846  -0.1565   0.6593   1.0000
   5.000   1.1844   0.01591   0.00862  -0.1546   0.5987   1.0000
   5.250   1.1999   0.01671   0.00880  -0.1515   0.4857   1.0000
   5.500   1.2131   0.01785   0.00943  -0.1486   0.3949   1.0000
   5.750   1.2232   0.01931   0.01038  -0.1456   0.2964   1.0000
   6.000   1.2313   0.02119   0.01149  -0.1426   0.1823   1.0000
   6.250   1.2403   0.02327   0.01281  -0.1400   0.0800   1.0000
   6.500   1.2513   0.02524   0.01436  -0.1374   0.0322   1.0000
   6.750   1.2672   0.02660   0.01580  -0.1353   0.0238   1.0000
   7.000   1.2820   0.02805   0.01740  -0.1330   0.0211   1.0000
   7.250   1.2969   0.02940   0.01899  -0.1308   0.0197   1.0000
   7.500   1.3102   0.03088   0.02076  -0.1284   0.0186   1.0000
   7.750   1.3219   0.03247   0.02255  -0.1258   0.0178   1.0000
   8.000   1.3331   0.03419   0.02444  -0.1232   0.0172   1.0000
   8.250   1.3452   0.03609   0.02650  -0.1208   0.0167   1.0000
   8.500   1.3596   0.03823   0.02879  -0.1189   0.0163   1.0000
   8.750   1.3772   0.04074   0.03148  -0.1175   0.0159   1.0000
   9.000   1.3984   0.04417   0.03508  -0.1170   0.0153   1.0000
   9.250   1.4145   0.04659   0.03790  -0.1152   0.0148   1.0000
   9.500   1.4267   0.04932   0.04106  -0.1131   0.0140   1.0000
   9.750   1.4346   0.05241   0.04457  -0.1105   0.0136   1.0000
  10.000   1.4373   0.05581   0.04839  -0.1074   0.0135   1.0000
  10.250   1.4346   0.05933   0.05231  -0.1040   0.0135   1.0000
  10.500   1.4276   0.06299   0.05635  -0.1005   0.0135   1.0000
  10.750   1.4173   0.06682   0.06054  -0.0973   0.0135   1.0000
  11.000   1.4038   0.07098   0.06512  -0.0944   0.0135   1.0000
  11.250   1.3882   0.07545   0.06991  -0.0922   0.0136   1.0000
  11.500   1.3711   0.08026   0.07502  -0.0909   0.0136   1.0000
  11.750   1.3528   0.08552   0.08056  -0.0905   0.0137   1.0000
  12.000   1.3333   0.09132   0.08662  -0.0912   0.0137   1.0000
  12.250   1.3133   0.09772   0.09318  -0.0931   0.0138   1.0000
  12.500   1.2931   0.10478   0.10045  -0.0962   0.0139   1.0000
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