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E221 (9.39%) (e221-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E221 (9.39%) (e221-il)
Reynolds number: 50,000
Max Cl/Cd: 33.68 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e221-il-50000-n5.txt
Download as CSV file: xf-e221-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E221  (9.39%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5238   0.11528   0.10837   0.0034   1.0000   0.0545
  -9.750  -0.5206   0.11096   0.10410   0.0016   1.0000   0.0516
  -9.500  -0.5368   0.10370   0.09696  -0.0070   1.0000   0.0460
  -9.250  -0.5274   0.10015   0.09343  -0.0062   1.0000   0.0451
  -9.000  -0.5239   0.09608   0.08940  -0.0075   1.0000   0.0442
  -8.750  -0.5230   0.09171   0.08509  -0.0096   1.0000   0.0434
  -8.500  -0.5237   0.08714   0.08060  -0.0124   1.0000   0.0427
  -8.250  -0.5273   0.08214   0.07567  -0.0160   1.0000   0.0419
  -8.000  -0.5320   0.07733   0.07089  -0.0189   1.0000   0.0411
  -7.750  -0.5353   0.07225   0.06580  -0.0216   1.0000   0.0404
  -7.500  -0.5381   0.06712   0.06059  -0.0238   1.0000   0.0396
  -7.250  -0.5391   0.06214   0.05545  -0.0253   1.0000   0.0389
  -7.000  -0.5377   0.05730   0.05038  -0.0261   1.0000   0.0383
  -6.750  -0.5332   0.05269   0.04546  -0.0262   1.0000   0.0378
  -6.500  -0.5256   0.04842   0.04082  -0.0258   1.0000   0.0376
  -6.250  -0.5149   0.04460   0.03658  -0.0249   1.0000   0.0376
  -6.000  -0.5016   0.04116   0.03272  -0.0239   1.0000   0.0378
  -5.750  -0.4860   0.03823   0.02940  -0.0227   1.0000   0.0386
  -5.500  -0.4687   0.03569   0.02649  -0.0214   1.0000   0.0408
  -5.250  -0.4499   0.03327   0.02357  -0.0200   1.0000   0.0433
  -5.000  -0.4294   0.03100   0.02079  -0.0185   1.0000   0.0455
  -4.750  -0.4091   0.02886   0.01848  -0.0172   1.0000   0.0474
  -4.500  -0.3891   0.02719   0.01672  -0.0158   1.0000   0.0504
  -4.250  -0.3689   0.02582   0.01513  -0.0143   1.0000   0.0562
  -4.000  -0.3507   0.02459   0.01390  -0.0127   1.0000   0.0641
  -3.750  -0.3326   0.02343   0.01268  -0.0111   1.0000   0.0759
  -3.500  -0.3147   0.02240   0.01159  -0.0096   1.0000   0.0984
  -3.250  -0.2972   0.02126   0.01068  -0.0084   1.0000   0.1408
  -3.000  -0.2637   0.01961   0.00978  -0.0105   0.9872   0.2645
  -2.750  -0.2320   0.01806   0.00933  -0.0118   0.9726   0.4852
  -2.500  -0.1603   0.01694   0.00933  -0.0165   0.9752   0.8664
  -2.250  -0.0627   0.01696   0.00869  -0.0289   0.9847   0.9995
  -2.000  -0.0176   0.01693   0.00826  -0.0332   0.9622   1.0000
  -1.750   0.0264   0.01691   0.00788  -0.0370   0.9417   1.0000
  -1.500   0.0667   0.01689   0.00755  -0.0398   0.9209   1.0000
  -1.250   0.1046   0.01689   0.00729  -0.0420   0.9015   1.0000
  -1.000   0.1369   0.01694   0.00711  -0.0430   0.8819   1.0000
  -0.750   0.1652   0.01703   0.00699  -0.0431   0.8626   1.0000
  -0.500   0.1915   0.01715   0.00692  -0.0427   0.8446   1.0000
  -0.250   0.2160   0.01729   0.00689  -0.0419   0.8277   1.0000
   0.000   0.2391   0.01747   0.00692  -0.0409   0.8108   1.0000
   0.250   0.2618   0.01766   0.00698  -0.0397   0.7944   1.0000
   0.500   0.2844   0.01785   0.00706  -0.0386   0.7787   1.0000
   0.750   0.3069   0.01806   0.00717  -0.0374   0.7634   1.0000
   1.000   0.3294   0.01828   0.00731  -0.0362   0.7486   1.0000
   1.250   0.3520   0.01850   0.00746  -0.0351   0.7341   1.0000
   1.500   0.3746   0.01873   0.00763  -0.0339   0.7197   1.0000
   1.750   0.3973   0.01897   0.00783  -0.0327   0.7056   1.0000
   2.000   0.4201   0.01922   0.00804  -0.0316   0.6915   1.0000
   2.250   0.4429   0.01946   0.00828  -0.0304   0.6775   1.0000
   2.500   0.4657   0.01971   0.00852  -0.0293   0.6635   1.0000
   2.750   0.4890   0.01997   0.00877  -0.0282   0.6494   1.0000
   3.000   0.5122   0.02023   0.00908  -0.0272   0.6353   1.0000
   3.250   0.5353   0.02050   0.00936  -0.0261   0.6209   1.0000
   3.500   0.5583   0.02077   0.00967  -0.0250   0.6063   1.0000
   3.750   0.5813   0.02105   0.01000  -0.0238   0.5913   1.0000
   4.000   0.6041   0.02134   0.01038  -0.0227   0.5760   1.0000
   4.250   0.6268   0.02164   0.01075  -0.0216   0.5602   1.0000
   4.500   0.6494   0.02193   0.01112  -0.0204   0.5440   1.0000
   4.750   0.6719   0.02222   0.01148  -0.0192   0.5274   1.0000
   5.000   0.6945   0.02250   0.01187  -0.0179   0.5105   1.0000
   5.250   0.7170   0.02276   0.01220  -0.0166   0.4934   1.0000
   5.500   0.7388   0.02311   0.01267  -0.0154   0.4742   1.0000
   5.750   0.7605   0.02346   0.01312  -0.0141   0.4544   1.0000
   6.000   0.7825   0.02375   0.01351  -0.0127   0.4349   1.0000
   6.250   0.8030   0.02419   0.01409  -0.0113   0.4121   1.0000
   6.500   0.8236   0.02458   0.01454  -0.0099   0.3895   1.0000
   6.750   0.8434   0.02504   0.01511  -0.0085   0.3649   1.0000
   7.000   0.8623   0.02560   0.01576  -0.0070   0.3388   1.0000
   7.250   0.8803   0.02623   0.01650  -0.0055   0.3119   1.0000
   7.500   0.8972   0.02697   0.01729  -0.0039   0.2841   1.0000
   7.750   0.9128   0.02785   0.01818  -0.0023   0.2558   1.0000
   8.000   0.9269   0.02889   0.01922  -0.0007   0.2280   1.0000
   8.250   0.9392   0.03010   0.02041   0.0010   0.2008   1.0000
   8.500   0.9498   0.03150   0.02178   0.0028   0.1757   1.0000
   8.750   0.9581   0.03308   0.02329   0.0046   0.1529   1.0000
   9.000   0.9641   0.03483   0.02508   0.0064   0.1293   1.0000
   9.250   0.9674   0.03670   0.02689   0.0081   0.1100   1.0000
   9.500   0.9696   0.03872   0.02892   0.0099   0.0934   1.0000
   9.750   0.9699   0.04082   0.03103   0.0118   0.0822   1.0000
  10.000   0.9686   0.04305   0.03316   0.0135   0.0743   1.0000
  10.250   0.9729   0.04541   0.03577   0.0150   0.0668   1.0000
  10.500   0.9751   0.04782   0.03810   0.0161   0.0622   1.0000
  10.750   0.9807   0.05044   0.04106   0.0171   0.0572   1.0000
  11.000   0.9830   0.05303   0.04377   0.0177   0.0536   1.0000
  11.250   0.9861   0.05573   0.04646   0.0182   0.0507   1.0000
  11.500   0.9871   0.05916   0.05027   0.0185   0.0485   1.0000
  11.750   0.9859   0.06284   0.05429   0.0184   0.0471   1.0000
  12.000   0.9804   0.06704   0.05876   0.0177   0.0460   1.0000
  12.250   0.9716   0.07173   0.06368   0.0163   0.0454   1.0000
  12.500   0.9593   0.07710   0.06928   0.0141   0.0451   1.0000
  12.750   0.9429   0.08340   0.07580   0.0110   0.0451   1.0000
  13.000   0.9217   0.09101   0.08360   0.0067   0.0452   1.0000
  13.250   0.8960   0.10028   0.09301   0.0011   0.0459   1.0000
  13.500   0.8666   0.11145   0.10428  -0.0057   0.0469   1.0000
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