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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 200,000
Max Cl/Cd: 59.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e226-il-200000.txt
Download as CSV file: xf-e226-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E226  (10.19%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4669   0.10562   0.10227  -0.0126   1.0000   0.0631
 -10.750  -0.4602   0.10237   0.09902  -0.0127   1.0000   0.0644
  -8.000  -0.7178   0.03431   0.02835  -0.0327   1.0000   0.0312
  -7.750  -0.7006   0.03319   0.02687  -0.0307   1.0000   0.0302
  -7.500  -0.6873   0.02986   0.02328  -0.0290   1.0000   0.0296
  -7.250  -0.6727   0.02721   0.02034  -0.0271   1.0000   0.0294
  -7.000  -0.6559   0.02512   0.01798  -0.0252   1.0000   0.0293
  -6.750  -0.6379   0.02340   0.01601  -0.0235   1.0000   0.0295
  -6.500  -0.6195   0.02213   0.01456  -0.0218   1.0000   0.0303
  -6.250  -0.6026   0.02016   0.01253  -0.0200   1.0000   0.0315
  -6.000  -0.5852   0.01899   0.01135  -0.0183   1.0000   0.0327
  -5.750  -0.5679   0.01796   0.01029  -0.0164   1.0000   0.0337
  -5.500  -0.5510   0.01706   0.00933  -0.0144   1.0000   0.0351
  -5.250  -0.5339   0.01628   0.00849  -0.0125   1.0000   0.0369
  -5.000  -0.5164   0.01559   0.00773  -0.0107   1.0000   0.0391
  -4.750  -0.4999   0.01470   0.00683  -0.0089   1.0000   0.0446
  -4.500  -0.4827   0.01367   0.00597  -0.0072   1.0000   0.0742
  -4.250  -0.4661   0.01252   0.00545  -0.0060   1.0000   0.1862
  -4.000  -0.4470   0.01212   0.00526  -0.0049   1.0000   0.2434
  -3.750  -0.4138   0.01168   0.00515  -0.0067   0.9960   0.3210
  -3.500  -0.3753   0.01130   0.00507  -0.0094   0.9896   0.4041
  -3.250  -0.3352   0.01099   0.00503  -0.0122   0.9838   0.4799
  -3.000  -0.2988   0.01072   0.00495  -0.0141   0.9759   0.5401
  -2.750  -0.2593   0.01051   0.00489  -0.0165   0.9699   0.5961
  -2.500  -0.2232   0.01030   0.00484  -0.0180   0.9619   0.6456
  -2.250  -0.1812   0.01013   0.00480  -0.0206   0.9571   0.6937
  -2.000  -0.1472   0.00998   0.00474  -0.0215   0.9482   0.7358
  -1.750  -0.1057   0.00984   0.00469  -0.0237   0.9434   0.7758
  -1.500  -0.0744   0.00973   0.00465  -0.0238   0.9335   0.8100
  -1.250  -0.0380   0.00963   0.00459  -0.0248   0.9266   0.8413
  -1.000  -0.0071   0.00957   0.00456  -0.0246   0.9163   0.8699
  -0.750   0.0248   0.00954   0.00453  -0.0245   0.9059   0.8952
  -0.500   0.0613   0.00951   0.00447  -0.0254   0.8967   0.9159
  -0.250   0.0991   0.00950   0.00442  -0.0267   0.8853   0.9333
   0.000   0.1396   0.00950   0.00438  -0.0286   0.8729   0.9480
   0.250   0.1825   0.00948   0.00431  -0.0312   0.8598   0.9601
   0.500   0.2259   0.00945   0.00422  -0.0340   0.8454   0.9715
   0.750   0.2725   0.00937   0.00410  -0.0376   0.8297   0.9809
   1.000   0.3177   0.00929   0.00396  -0.0410   0.8124   0.9909
   1.250   0.3613   0.00919   0.00379  -0.0442   0.7941   1.0000
   1.500   0.3803   0.00915   0.00370  -0.0425   0.7731   1.0000
   1.750   0.4001   0.00914   0.00362  -0.0410   0.7529   1.0000
   2.000   0.4204   0.00916   0.00356  -0.0394   0.7326   1.0000
   2.250   0.4410   0.00921   0.00355  -0.0379   0.7108   1.0000
   2.500   0.4621   0.00929   0.00356  -0.0365   0.6896   1.0000
   2.750   0.4834   0.00938   0.00360  -0.0351   0.6660   1.0000
   3.000   0.5050   0.00951   0.00365  -0.0338   0.6429   1.0000
   3.250   0.5267   0.00965   0.00372  -0.0324   0.6181   1.0000
   3.500   0.5486   0.00981   0.00383  -0.0312   0.5921   1.0000
   3.750   0.5706   0.01000   0.00395  -0.0299   0.5656   1.0000
   4.000   0.5925   0.01022   0.00409  -0.0287   0.5377   1.0000
   4.250   0.6144   0.01047   0.00426  -0.0274   0.5087   1.0000
   4.500   0.6362   0.01073   0.00447  -0.0262   0.4781   1.0000
   4.750   0.6577   0.01104   0.00468  -0.0249   0.4446   1.0000
   5.000   0.6790   0.01139   0.00492  -0.0237   0.4102   1.0000
   5.250   0.7006   0.01176   0.00522  -0.0225   0.3740   1.0000
   5.500   0.7215   0.01221   0.00553  -0.0213   0.3358   1.0000
   5.750   0.7421   0.01271   0.00588  -0.0201   0.2929   1.0000
   6.000   0.7624   0.01329   0.00628  -0.0190   0.2466   1.0000
   6.250   0.7825   0.01394   0.00675  -0.0179   0.2004   1.0000
   6.500   0.8024   0.01466   0.00726  -0.0169   0.1576   1.0000
   6.750   0.8223   0.01543   0.00786  -0.0158   0.1224   1.0000
   7.000   0.8404   0.01647   0.00868  -0.0145   0.0771   1.0000
   7.250   0.8533   0.01821   0.01017  -0.0122   0.0427   1.0000
   7.500   0.8697   0.01945   0.01142  -0.0105   0.0355   1.0000
   7.750   0.8876   0.02049   0.01252  -0.0090   0.0317   1.0000
   8.000   0.9023   0.02195   0.01399  -0.0072   0.0295   1.0000
   8.250   0.9187   0.02351   0.01562  -0.0056   0.0284   1.0000
   8.500   0.9378   0.02488   0.01711  -0.0042   0.0274   1.0000
   8.750   0.9573   0.02646   0.01881  -0.0030   0.0266   1.0000
   9.000   0.9771   0.02825   0.02077  -0.0019   0.0261   1.0000
   9.250   0.9961   0.03016   0.02287  -0.0007   0.0255   1.0000
   9.500   1.0137   0.03201   0.02491   0.0004   0.0248   1.0000
   9.750   1.0293   0.03360   0.02662   0.0017   0.0237   1.0000
  10.000   1.0435   0.03579   0.02900   0.0029   0.0231   1.0000
  10.250   1.0542   0.03846   0.03197   0.0046   0.0231   1.0000
  10.500   1.0603   0.04139   0.03523   0.0066   0.0231   1.0000
  10.750   1.0587   0.04485   0.03913   0.0093   0.0236   1.0000
  11.000   1.0373   0.04900   0.04382   0.0135   0.0246   1.0000
  11.250   1.0172   0.05283   0.04798   0.0164   0.0251   1.0000
  11.500   0.9955   0.05701   0.05244   0.0177   0.0255   1.0000
  11.750   0.9733   0.06162   0.05728   0.0175   0.0258   1.0000
  12.000   0.9512   0.06683   0.06269   0.0158   0.0262   1.0000
  12.250   0.9275   0.07303   0.06907   0.0125   0.0266   1.0000
  12.500   0.9023   0.08043   0.07663   0.0075   0.0267   1.0000
  12.750   0.8768   0.08912   0.08545   0.0012   0.0272   1.0000
  13.000   0.8456   0.10059   0.09704  -0.0070   0.0276   1.0000
  13.250   0.8224   0.11123   0.10770  -0.0135   0.0283   1.0000
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