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E61 (5.64%) (e61-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E61 (5.64%) (e61-il)
Reynolds number: 50,000
Max Cl/Cd: 46.87 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e61-il-50000.txt
Download as CSV file: xf-e61-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E61  (5.64%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3478   0.12034   0.11426  -0.0195   1.0000   0.0963
  -6.750  -0.3617   0.12085   0.11489  -0.0180   1.0000   0.0970
  -6.500  -0.3707   0.12135   0.11551  -0.0192   1.0000   0.0975
  -6.250  -0.3547   0.11319   0.10734  -0.0145   1.0000   0.1028
  -6.000  -0.3574   0.11143   0.10564  -0.0134   1.0000   0.1061
  -5.750  -0.3622   0.11056   0.10486  -0.0138   1.0000   0.1096
  -5.500  -0.3644   0.11059   0.10498  -0.0174   1.0000   0.1111
  -5.250  -0.3620   0.10613   0.10059  -0.0144   1.0000   0.1136
  -5.000  -0.3591   0.10303   0.09753  -0.0125   1.0000   0.1187
  -4.750  -0.3548   0.10142   0.09596  -0.0151   1.0000   0.1235
  -4.500  -0.3443   0.09956   0.09416  -0.0211   1.0000   0.1262
  -4.250  -0.3441   0.09563   0.09021  -0.0162   1.0000   0.1301
  -4.000  -0.3331   0.09326   0.08786  -0.0192   1.0000   0.1370
  -3.750  -0.3187   0.09021   0.08483  -0.0234   1.0000   0.1415
  -3.500  -0.3106   0.08718   0.08183  -0.0228   1.0000   0.1490
  -3.250  -0.2906   0.08404   0.07869  -0.0279   1.0000   0.1563
  -3.000  -0.2624   0.08100   0.07561  -0.0352   1.0000   0.1685
  -2.750  -0.2361   0.07787   0.07244  -0.0405   1.0000   0.1820
  -2.500  -0.2312   0.07475   0.06936  -0.0374   1.0000   0.1907
  -2.250  -0.1951   0.07141   0.06596  -0.0454   1.0000   0.2108
  -2.000  -0.1628   0.06853   0.06302  -0.0511   1.0000   0.2376
  -1.750  -0.1430   0.06569   0.06019  -0.0524   1.0000   0.2658
  -0.250   0.1943   0.04664   0.03967  -0.1110   1.0000   0.2560
   0.000   0.1597   0.04679   0.04045  -0.0969   1.0000   0.3963
   0.250   0.1207   0.04586   0.03999  -0.0800   1.0000   0.5224
   0.500   0.4048   0.03979   0.03001  -0.1387   1.0000   0.1328
   0.750   0.4407   0.03942   0.02919  -0.1406   1.0000   0.1356
   1.000   0.4701   0.03929   0.02869  -0.1412   1.0000   0.1437
   1.250   0.4986   0.03937   0.02863  -0.1419   1.0000   0.1696
   1.500   0.5436   0.03706   0.02810  -0.1443   1.0000   1.0000
   1.750   0.5637   0.03820   0.02872  -0.1441   1.0000   1.0000
   2.000   0.5827   0.03941   0.02963  -0.1439   1.0000   1.0000
   2.250   0.6011   0.04068   0.03069  -0.1438   1.0000   1.0000
   2.500   0.6190   0.04203   0.03186  -0.1438   1.0000   1.0000
   2.750   0.6362   0.04345   0.03316  -0.1437   1.0000   1.0000
   3.000   0.6578   0.04507   0.03469  -0.1447   0.9966   1.0000
   3.250   0.7075   0.04704   0.03655  -0.1506   0.9752   1.0000
   3.500   0.7502   0.04858   0.03805  -0.1548   0.9568   1.0000
   3.750   0.7879   0.04985   0.03930  -0.1579   0.9388   1.0000
   4.250   0.8614   0.05205   0.04157  -0.1633   0.9029   1.0000
   4.500   0.9015   0.05294   0.04261  -0.1661   0.8852   1.0000
   4.750   0.9403   0.05372   0.04349  -0.1684   0.8671   1.0000
   5.000   0.9738   0.05444   0.04436  -0.1699   0.8473   1.0000
   5.250   1.0212   0.05459   0.04470  -0.1727   0.8294   1.0000
   5.500   1.0501   0.05514   0.04555  -0.1730   0.8075   1.0000
   5.750   1.1010   0.05452   0.04522  -0.1754   0.7887   1.0000
   6.000   1.1331   0.05450   0.04547  -0.1753   0.7654   1.0000
   6.250   1.1987   0.05199   0.04340  -0.1777   0.7465   1.0000
   6.500   1.2406   0.05035   0.04227  -0.1771   0.7214   1.0000
   6.750   1.3010   0.04635   0.03885  -0.1768   0.6964   1.0000
   7.000   1.4068   0.03741   0.03091  -0.1787   0.6604   1.0000
   7.250   1.4676   0.03252   0.02647  -0.1766   0.5920   1.0000
   7.500   1.4848   0.03168   0.02541  -0.1706   0.5026   1.0000
   7.750   1.4828   0.03302   0.02608  -0.1635   0.4083   1.0000
   8.000   1.4713   0.03554   0.02788  -0.1564   0.3251   1.0000
   8.250   1.4577   0.03888   0.03039  -0.1498   0.2468   1.0000
   8.500   1.4417   0.04248   0.03332  -0.1439   0.1810   1.0000
   8.750   1.4325   0.04650   0.03674  -0.1392   0.1237   1.0000
   9.250   1.5329   0.05635   0.04642  -0.1428   0.0651   1.0000
   9.500   1.5786   0.06306   0.05357  -0.1448   0.0613   1.0000
   9.750   1.5921   0.06807   0.05921  -0.1424   0.0608   1.0000
  10.000   1.5970   0.07314   0.06484  -0.1393   0.0609   1.0000
  10.250   1.5963   0.07821   0.07039  -0.1359   0.0612   1.0000
  10.500   1.5920   0.08345   0.07603  -0.1326   0.0617   1.0000
  10.750   1.5882   0.08927   0.08215  -0.1298   0.0623   1.0000
  11.000   1.5689   0.09239   0.08572  -0.1248   0.0630   1.0000
  11.250   1.5362   0.09550   0.08930  -0.1198   0.0638   1.0000
  11.500   1.5023   0.10001   0.09422  -0.1165   0.0647   1.0000
  11.750   1.4702   0.10553   0.10009  -0.1152   0.0655   1.0000
  12.000   1.4390   0.11185   0.10671  -0.1158   0.0665   1.0000
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