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E385 (8.41%) (e385-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E385 (8.41%) (e385-il)
Reynolds number: 200,000
Max Cl/Cd: 96.82 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e385-il-200000.txt
Download as CSV file: xf-e385-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2628   0.10928   0.10599  -0.0353   1.0000   0.0272
  -8.500  -0.2719   0.10838   0.10517  -0.0330   1.0000   0.0277
  -8.250  -0.2791   0.10762   0.10449  -0.0326   0.9989   0.0282
  -8.000  -0.2582   0.10443   0.10130  -0.0417   0.9929   0.0286
  -7.750  -0.2361   0.10090   0.09777  -0.0503   0.9860   0.0288
  -7.500  -0.2181   0.09590   0.09280  -0.0565   0.9780   0.0291
  -7.250  -0.1970   0.09017   0.08704  -0.0557   0.9768   0.0302
  -7.000  -0.1724   0.08612   0.08298  -0.0593   0.9731   0.0317
  -6.750  -0.1526   0.08258   0.07943  -0.0638   0.9639   0.0331
  -6.500  -0.1231   0.07820   0.07503  -0.0716   0.9586   0.0351
  -6.250  -0.0860   0.07395   0.07075  -0.0865   0.9468   0.0382
  -6.000  -0.0551   0.06763   0.06441  -0.0981   0.9380   0.0397
  -5.750  -0.0347   0.06429   0.06107  -0.0975   0.9340   0.0413
  -5.500  -0.0053   0.06061   0.05735  -0.1028   0.9274   0.0434
  -5.250   0.0293   0.05635   0.05303  -0.1111   0.9192   0.0466
  -5.000   0.0975   0.05041   0.04666  -0.1330   0.9077   0.0510
  -4.750   0.1144   0.04524   0.04158  -0.1339   0.9020   0.0528
  -4.500   0.1365   0.04287   0.03918  -0.1349   0.8914   0.0552
  -4.250   0.1911   0.03942   0.03510  -0.1458   0.8816   0.0642
  -4.000   0.2147   0.03443   0.03016  -0.1483   0.8743   0.0666
  -3.750   0.2396   0.03238   0.02806  -0.1492   0.8640   0.0701
  -3.500   0.2785   0.02902   0.02424  -0.1540   0.8559   0.0809
  -3.250   0.3071   0.02706   0.02217  -0.1551   0.8473   0.0858
  -3.000   0.3399   0.02479   0.01959  -0.1574   0.8387   0.0976
  -2.500   0.4236   0.01661   0.00950  -0.1604   0.8245   0.0384
  -2.250   0.4544   0.01528   0.00789  -0.1607   0.8174   0.0384
  -2.000   0.4834   0.01417   0.00664  -0.1608   0.8094   0.0396
  -1.750   0.5135   0.01331   0.00573  -0.1612   0.8026   0.0443
  -1.500   0.5427   0.01282   0.00523  -0.1615   0.7947   0.0591
  -1.250   0.5750   0.01184   0.00471  -0.1626   0.7883   0.2076
  -1.000   0.6031   0.01104   0.00489  -0.1633   0.7808   0.5196
  -0.750   0.6193   0.01039   0.00495  -0.1601   0.7744   0.8109
  -0.500   0.6414   0.01023   0.00478  -0.1584   0.7673   1.0000
  -0.250   0.6704   0.01036   0.00470  -0.1586   0.7607   1.0000
   0.000   0.6989   0.01053   0.00469  -0.1587   0.7543   1.0000
   0.250   0.7271   0.01068   0.00471  -0.1588   0.7476   1.0000
   0.500   0.7559   0.01084   0.00472  -0.1589   0.7419   1.0000
   0.750   0.7833   0.01102   0.00482  -0.1589   0.7348   1.0000
   1.000   0.8122   0.01118   0.00484  -0.1591   0.7295   1.0000
   1.250   0.8393   0.01138   0.00500  -0.1590   0.7225   1.0000
   1.500   0.8676   0.01154   0.00509  -0.1591   0.7167   1.0000
   1.750   0.8952   0.01175   0.00525  -0.1591   0.7106   1.0000
   2.000   0.9227   0.01193   0.00540  -0.1590   0.7041   1.0000
   2.250   0.9512   0.01213   0.00551  -0.1591   0.6990   1.0000
   2.500   0.9776   0.01233   0.00576  -0.1590   0.6917   1.0000
   2.750   1.0059   0.01250   0.00587  -0.1590   0.6861   1.0000
   3.000   1.0322   0.01272   0.00612  -0.1588   0.6788   1.0000
   3.250   1.0600   0.01287   0.00623  -0.1587   0.6723   1.0000
   3.500   1.0863   0.01307   0.00649  -0.1585   0.6646   1.0000
   3.750   1.1140   0.01321   0.00661  -0.1583   0.6577   1.0000
   4.000   1.1399   0.01340   0.00686  -0.1580   0.6495   1.0000
   4.250   1.1677   0.01353   0.00695  -0.1579   0.6423   1.0000
   4.500   1.1929   0.01369   0.00720  -0.1574   0.6329   1.0000
   4.750   1.2199   0.01382   0.00737  -0.1571   0.6248   1.0000
   5.000   1.2457   0.01395   0.00756  -0.1567   0.6155   1.0000
   5.250   1.2711   0.01409   0.00779  -0.1562   0.6058   1.0000
   5.500   1.2973   0.01420   0.00794  -0.1557   0.5960   1.0000
   5.750   1.3226   0.01428   0.00809  -0.1551   0.5847   1.0000
   6.000   1.3469   0.01440   0.00831  -0.1544   0.5724   1.0000
   6.250   1.3711   0.01450   0.00851  -0.1536   0.5589   1.0000
   6.500   1.3942   0.01454   0.00857  -0.1524   0.5402   1.0000
   6.750   1.4145   0.01461   0.00867  -0.1508   0.5123   1.0000
   7.000   1.4343   0.01484   0.00890  -0.1492   0.4812   1.0000
   7.250   1.4529   0.01523   0.00925  -0.1475   0.4439   1.0000
   7.500   1.4653   0.01603   0.00978  -0.1449   0.3816   1.0000
   7.750   1.4720   0.01735   0.01067  -0.1416   0.3077   1.0000
   8.000   1.4765   0.01893   0.01186  -0.1382   0.2431   1.0000
   8.250   1.4796   0.02060   0.01318  -0.1347   0.1845   1.0000
   8.500   1.4773   0.02248   0.01468  -0.1305   0.1255   1.0000
   8.750   1.4648   0.02499   0.01669  -0.1250   0.0638   1.0000
   9.000   1.4556   0.02749   0.01897  -0.1201   0.0390   1.0000
   9.250   1.4556   0.02944   0.02100  -0.1168   0.0328   1.0000
   9.500   1.4563   0.03144   0.02307  -0.1139   0.0292   1.0000
   9.750   1.4537   0.03385   0.02561  -0.1111   0.0271   1.0000
  10.000   1.4570   0.03588   0.02779  -0.1089   0.0257   1.0000
  10.250   1.4589   0.03817   0.03021  -0.1069   0.0246   1.0000
  10.500   1.4609   0.04057   0.03272  -0.1051   0.0237   1.0000
  10.750   1.4633   0.04305   0.03530  -0.1034   0.0229   1.0000
  11.000   1.4664   0.04557   0.03792  -0.1018   0.0222   1.0000
  11.250   1.4710   0.04813   0.04055  -0.1002   0.0216   1.0000
  11.500   1.4796   0.05065   0.04313  -0.0986   0.0210   1.0000
  11.750   1.4984   0.05304   0.04561  -0.0969   0.0206   1.0000
  12.000   1.5249   0.05590   0.04868  -0.0957   0.0202   1.0000
  12.250   1.5310   0.05842   0.05146  -0.0944   0.0199   1.0000
  12.500   1.5361   0.06124   0.05454  -0.0932   0.0195   1.0000
  12.750   1.5399   0.06449   0.05807  -0.0921   0.0192   1.0000
  13.000   1.5418   0.06842   0.06231  -0.0909   0.0192   1.0000
  13.250   1.5392   0.07280   0.06700  -0.0900   0.0193   1.0000
  13.500   1.5321   0.07758   0.07208  -0.0893   0.0194   1.0000
  13.750   1.5215   0.08277   0.07757  -0.0890   0.0195   1.0000
  14.000   1.5084   0.08843   0.08350  -0.0892   0.0197   1.0000
  14.250   1.4932   0.09437   0.08971  -0.0899   0.0198   1.0000
  14.500   1.4764   0.10107   0.09666  -0.0911   0.0200   1.0000
  14.750   1.4700   0.10651   0.10229  -0.0920   0.0204   1.0000
  15.000   1.4581   0.11136   0.10735  -0.0940   0.0206   1.0000
  15.250   1.4415   0.11750   0.11373  -0.0968   0.0209   1.0000
  15.500   1.4214   0.12483   0.12134  -0.1009   0.0212   1.0000
  15.750   1.3894   0.13553   0.13238  -0.1078   0.0219   1.0000
  16.000   1.3537   0.14869   0.14585  -0.1172   0.0224   1.0000
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