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E205 (10.48%) (e205-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E205 (10.48%) (e205-il)
Reynolds number: 50,000
Max Cl/Cd: 34.53 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e205-il-50000-n5.txt
Download as CSV file: xf-e205-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E205  (10.48%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4122   0.12371   0.11661  -0.0161   1.0000   0.1101
 -10.250  -0.4194   0.12136   0.11436  -0.0191   1.0000   0.1130
 -10.000  -0.4216   0.11834   0.11141  -0.0215   1.0000   0.1135
  -9.750  -0.4011   0.11285   0.10588  -0.0201   1.0000   0.1072
  -9.500  -0.4147   0.10406   0.09712  -0.0279   1.0000   0.0589
  -9.250  -0.4057   0.10050   0.09359  -0.0276   1.0000   0.0572
  -9.000  -0.4026   0.09674   0.08988  -0.0287   1.0000   0.0556
  -8.750  -0.4020   0.09284   0.08606  -0.0302   1.0000   0.0542
  -8.500  -0.4038   0.08876   0.08207  -0.0321   1.0000   0.0528
  -8.250  -0.4081   0.08453   0.07794  -0.0344   1.0000   0.0515
  -8.000  -0.4174   0.07986   0.07339  -0.0374   1.0000   0.0502
  -7.500  -0.4412   0.06733   0.06075  -0.0458   1.0000   0.0466
  -7.250  -0.4419   0.06355   0.05692  -0.0459   1.0000   0.0463
  -7.000  -0.4422   0.05985   0.05315  -0.0456   1.0000   0.0460
  -6.750  -0.4420   0.05621   0.04938  -0.0450   1.0000   0.0459
  -6.500  -0.4411   0.05258   0.04553  -0.0441   1.0000   0.0461
  -6.250  -0.4389   0.04921   0.04185  -0.0428   1.0000   0.0464
  -6.000  -0.4355   0.04614   0.03850  -0.0411   1.0000   0.0471
  -5.750  -0.4302   0.04382   0.03605  -0.0393   1.0000   0.0483
  -5.500  -0.4238   0.04191   0.03403  -0.0373   1.0000   0.0494
  -5.250  -0.3996   0.03891   0.03061  -0.0387   0.9920   0.0506
  -5.000  -0.3638   0.03552   0.02663  -0.0415   0.9791   0.0513
  -4.750  -0.3274   0.03271   0.02327  -0.0439   0.9663   0.0527
  -4.500  -0.2895   0.03032   0.02039  -0.0460   0.9541   0.0547
  -4.250  -0.2504   0.02827   0.01789  -0.0480   0.9425   0.0577
  -4.000  -0.2136   0.02674   0.01617  -0.0498   0.9299   0.0637
  -3.750  -0.1760   0.02543   0.01462  -0.0515   0.9175   0.0739
  -3.500  -0.1393   0.02410   0.01318  -0.0530   0.9052   0.0873
  -3.000  -0.0701   0.02153   0.01123  -0.0563   0.8804   0.2231
  -2.750  -0.0406   0.02036   0.01061  -0.0568   0.8679   0.3504
  -2.500  -0.0155   0.01929   0.01028  -0.0558   0.8559   0.5241
  -2.250   0.0235   0.01836   0.01018  -0.0555   0.8451   0.7829
  -2.000   0.1375   0.01796   0.00926  -0.0705   0.8412   0.9927
  -1.750   0.1697   0.01795   0.00886  -0.0716   0.8272   1.0000
  -1.500   0.1940   0.01803   0.00860  -0.0711   0.8130   1.0000
  -1.250   0.2176   0.01815   0.00843  -0.0704   0.7995   1.0000
  -1.000   0.2408   0.01831   0.00832  -0.0696   0.7867   1.0000
  -0.750   0.2639   0.01849   0.00825  -0.0688   0.7746   1.0000
  -0.500   0.2872   0.01868   0.00823  -0.0680   0.7633   1.0000
  -0.250   0.3112   0.01887   0.00821  -0.0672   0.7531   1.0000
   0.000   0.3343   0.01910   0.00828  -0.0663   0.7425   1.0000
   0.250   0.3568   0.01938   0.00840  -0.0654   0.7320   1.0000
   0.500   0.3805   0.01963   0.00850  -0.0646   0.7228   1.0000
   0.750   0.4047   0.01990   0.00865  -0.0639   0.7136   1.0000
   1.000   0.4277   0.02023   0.00890  -0.0632   0.7039   1.0000
   1.250   0.4525   0.02049   0.00904  -0.0626   0.6959   1.0000
   1.500   0.4754   0.02086   0.00935  -0.0618   0.6866   1.0000
   1.750   0.4989   0.02121   0.00966  -0.0611   0.6781   1.0000
   2.000   0.5234   0.02153   0.00992  -0.0604   0.6702   1.0000
   2.250   0.5457   0.02197   0.01036  -0.0597   0.6613   1.0000
   2.500   0.5712   0.02225   0.01059  -0.0590   0.6544   1.0000
   2.750   0.5925   0.02277   0.01116  -0.0582   0.6451   1.0000
   3.000   0.6171   0.02312   0.01150  -0.0575   0.6380   1.0000
   3.250   0.6391   0.02362   0.01204  -0.0567   0.6292   1.0000
   3.500   0.6623   0.02407   0.01253  -0.0560   0.6214   1.0000
   3.750   0.6856   0.02451   0.01304  -0.0552   0.6135   1.0000
   4.000   0.7072   0.02506   0.01368  -0.0544   0.6049   1.0000
   4.250   0.7321   0.02542   0.01407  -0.0537   0.5977   1.0000
   4.500   0.7521   0.02607   0.01484  -0.0527   0.5882   1.0000
   4.750   0.7771   0.02641   0.01524  -0.0519   0.5808   1.0000
   5.000   0.7977   0.02700   0.01601  -0.0509   0.5710   1.0000
   5.250   0.8186   0.02756   0.01670  -0.0499   0.5614   1.0000
   5.500   0.8453   0.02772   0.01693  -0.0491   0.5534   1.0000
   5.750   0.8639   0.02836   0.01774  -0.0479   0.5420   1.0000
   6.000   0.8840   0.02887   0.01846  -0.0466   0.5307   1.0000
   6.250   0.9059   0.02922   0.01896  -0.0454   0.5195   1.0000
   6.500   0.9292   0.02940   0.01928  -0.0442   0.5081   1.0000
   6.750   0.9526   0.02951   0.01953  -0.0430   0.4957   1.0000
   7.000   0.9739   0.02968   0.01987  -0.0415   0.4819   1.0000
   7.250   0.9925   0.02997   0.02040  -0.0398   0.4665   1.0000
   7.500   1.0097   0.03027   0.02091  -0.0379   0.4495   1.0000
   7.750   1.0274   0.03044   0.02128  -0.0360   0.4314   1.0000
   8.000   1.0470   0.03036   0.02134  -0.0341   0.4120   1.0000
   8.250   1.0596   0.03078   0.02196  -0.0317   0.3893   1.0000
   8.500   1.0729   0.03107   0.02237  -0.0293   0.3644   1.0000
   8.750   1.0836   0.03154   0.02298  -0.0268   0.3365   1.0000
   9.000   1.0913   0.03225   0.02370  -0.0240   0.3058   1.0000
   9.250   1.0955   0.03322   0.02460  -0.0211   0.2743   1.0000
   9.500   1.0948   0.03456   0.02580  -0.0179   0.2454   1.0000
   9.750   1.0912   0.03629   0.02740  -0.0149   0.2196   1.0000
  10.000   1.0870   0.03836   0.02936  -0.0125   0.1971   1.0000
  10.250   1.0821   0.04074   0.03164  -0.0106   0.1774   1.0000
  10.500   1.0775   0.04334   0.03414  -0.0092   0.1603   1.0000
  10.750   1.0738   0.04610   0.03690  -0.0082   0.1437   1.0000
  11.000   1.0698   0.04903   0.03981  -0.0075   0.1287   1.0000
  11.250   1.0661   0.05207   0.04283  -0.0069   0.1151   1.0000
  11.500   1.0614   0.05533   0.04608  -0.0067   0.1021   1.0000
  11.750   1.0563   0.05875   0.04949  -0.0068   0.0904   1.0000
  12.000   1.0504   0.06238   0.05309  -0.0071   0.0797   1.0000
  12.250   1.0457   0.06598   0.05674  -0.0076   0.0710   1.0000
  12.500   1.0430   0.06957   0.06046  -0.0079   0.0627   1.0000
  12.750   1.0395   0.07322   0.06408  -0.0083   0.0568   1.0000
  13.000   1.0386   0.07681   0.06789  -0.0087   0.0513   1.0000
  13.250   1.0367   0.08034   0.07138  -0.0091   0.0476   1.0000
  13.500   1.0386   0.08395   0.07525  -0.0090   0.0446   1.0000
  13.750   1.0377   0.08803   0.07960  -0.0096   0.0422   1.0000
  14.000   1.0351   0.09235   0.08411  -0.0106   0.0405   1.0000
  14.250   1.0314   0.09677   0.08867  -0.0119   0.0389   1.0000
  14.500   1.0292   0.10095   0.09290  -0.0132   0.0374   1.0000
  14.750   1.0221   0.10641   0.09852  -0.0153   0.0366   1.0000
  15.000   1.0094   0.11327   0.10564  -0.0187   0.0363   1.0000
  15.250   0.9959   0.12068   0.11327  -0.0225   0.0362   1.0000
  15.500   0.9794   0.12924   0.12203  -0.0273   0.0362   1.0000
  15.750   0.9638   0.13816   0.13108  -0.0323   0.0365   1.0000
  16.000   0.9493   0.14737   0.14037  -0.0375   0.0368   1.0000
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