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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 50,000
Max Cl/Cd: 32.2 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e226-il-50000-n5.txt
Download as CSV file: xf-e226-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5882   0.09754   0.09039  -0.0176   1.0000   0.0431
 -10.250  -0.5951   0.09103   0.08394  -0.0213   1.0000   0.0426
 -10.000  -0.6057   0.08369   0.07664  -0.0260   1.0000   0.0418
  -9.750  -0.6229   0.07597   0.06893  -0.0319   1.0000   0.0409
  -9.500  -0.6457   0.06931   0.06222  -0.0367   1.0000   0.0401
  -9.250  -0.6674   0.06442   0.05722  -0.0380   1.0000   0.0394
  -9.000  -0.6824   0.05988   0.05247  -0.0384   1.0000   0.0392
  -8.750  -0.6897   0.05587   0.04819  -0.0381   1.0000   0.0395
  -8.500  -0.6918   0.05215   0.04415  -0.0373   1.0000   0.0402
  -8.250  -0.6894   0.04865   0.04029  -0.0363   1.0000   0.0410
  -8.000  -0.6829   0.04532   0.03655  -0.0352   1.0000   0.0418
  -7.750  -0.6729   0.04217   0.03295  -0.0338   1.0000   0.0428
  -7.500  -0.6592   0.03929   0.02964  -0.0325   1.0000   0.0436
  -7.250  -0.6425   0.03669   0.02660  -0.0311   1.0000   0.0446
  -7.000  -0.6242   0.03439   0.02401  -0.0297   1.0000   0.0460
  -6.750  -0.6062   0.03249   0.02203  -0.0284   1.0000   0.0480
  -6.500  -0.5880   0.03087   0.02028  -0.0270   1.0000   0.0515
  -6.250  -0.5690   0.02935   0.01851  -0.0253   1.0000   0.0570
  -6.000  -0.5524   0.02790   0.01709  -0.0238   1.0000   0.0634
  -5.750  -0.5355   0.02641   0.01554  -0.0220   1.0000   0.0723
  -5.500  -0.5193   0.02491   0.01405  -0.0203   1.0000   0.0922
  -5.250  -0.5036   0.02341   0.01290  -0.0189   1.0000   0.1375
  -5.000  -0.4884   0.02216   0.01212  -0.0176   1.0000   0.2118
  -4.750  -0.4717   0.02124   0.01143  -0.0160   1.0000   0.2735
  -4.500  -0.4543   0.02053   0.01088  -0.0145   1.0000   0.3306
  -4.250  -0.4370   0.01995   0.01039  -0.0127   1.0000   0.3843
  -4.000  -0.4199   0.01945   0.01001  -0.0107   1.0000   0.4342
  -3.750  -0.4026   0.01904   0.00970  -0.0086   1.0000   0.4834
  -3.500  -0.3852   0.01869   0.00944  -0.0065   1.0000   0.5322
  -3.250  -0.3679   0.01840   0.00920  -0.0043   1.0000   0.5800
  -3.000  -0.3506   0.01817   0.00906  -0.0020   1.0000   0.6270
  -2.750  -0.3334   0.01800   0.00895   0.0005   1.0000   0.6732
  -2.500  -0.3160   0.01789   0.00889   0.0029   1.0000   0.7196
  -2.250  -0.2976   0.01783   0.00885   0.0053   1.0000   0.7666
  -2.000  -0.2759   0.01784   0.00886   0.0070   1.0000   0.8152
  -1.750  -0.2463   0.01791   0.00888   0.0070   1.0000   0.8659
  -1.500  -0.2019   0.01805   0.00887   0.0039   1.0000   0.9149
  -1.250  -0.1384   0.01823   0.00884  -0.0033   0.9955   0.9559
  -1.000  -0.0697   0.01833   0.00872  -0.0120   0.9897   0.9881
  -0.750  -0.0193   0.01841   0.00862  -0.0176   0.9785   1.0000
  -0.500   0.0221   0.01849   0.00856  -0.0214   0.9640   1.0000
  -0.250   0.0635   0.01858   0.00853  -0.0250   0.9497   1.0000
   0.000   0.1053   0.01865   0.00852  -0.0284   0.9357   1.0000
   0.250   0.1475   0.01870   0.00851  -0.0317   0.9216   1.0000
   0.500   0.1867   0.01873   0.00850  -0.0342   0.9065   1.0000
   0.750   0.2231   0.01875   0.00851  -0.0360   0.8906   1.0000
   1.000   0.2573   0.01877   0.00853  -0.0373   0.8740   1.0000
   1.250   0.2896   0.01879   0.00855  -0.0380   0.8570   1.0000
   1.500   0.3205   0.01880   0.00858  -0.0383   0.8397   1.0000
   1.750   0.3480   0.01884   0.00864  -0.0380   0.8212   1.0000
   2.000   0.3728   0.01892   0.00874  -0.0371   0.8013   1.0000
   2.250   0.3985   0.01897   0.00881  -0.0362   0.7820   1.0000
   2.500   0.4246   0.01900   0.00889  -0.0352   0.7631   1.0000
   2.750   0.4466   0.01914   0.00905  -0.0337   0.7412   1.0000
   3.000   0.4709   0.01921   0.00915  -0.0324   0.7203   1.0000
   3.250   0.4937   0.01934   0.00932  -0.0310   0.6977   1.0000
   3.500   0.5176   0.01945   0.00948  -0.0296   0.6750   1.0000
   3.750   0.5402   0.01962   0.00969  -0.0281   0.6501   1.0000
   4.000   0.5634   0.01978   0.00988  -0.0266   0.6250   1.0000
   4.250   0.5865   0.01997   0.01011  -0.0251   0.5988   1.0000
   4.500   0.6086   0.02022   0.01039  -0.0235   0.5704   1.0000
   4.750   0.6306   0.02050   0.01069  -0.0220   0.5407   1.0000
   5.000   0.6523   0.02082   0.01102  -0.0204   0.5099   1.0000
   5.250   0.6732   0.02121   0.01144  -0.0188   0.4767   1.0000
   5.500   0.6936   0.02165   0.01189  -0.0172   0.4420   1.0000
   5.750   0.7135   0.02216   0.01236  -0.0156   0.4069   1.0000
   6.000   0.7327   0.02276   0.01295  -0.0140   0.3698   1.0000
   6.250   0.7511   0.02346   0.01361  -0.0124   0.3328   1.0000
   6.500   0.7688   0.02426   0.01438  -0.0108   0.2946   1.0000
   6.750   0.7854   0.02519   0.01521  -0.0092   0.2580   1.0000
   7.000   0.8016   0.02625   0.01622  -0.0077   0.2212   1.0000
   7.250   0.8165   0.02747   0.01734  -0.0061   0.1880   1.0000
   7.500   0.8307   0.02887   0.01864  -0.0045   0.1567   1.0000
   7.750   0.8434   0.03042   0.02016  -0.0029   0.1257   1.0000
   8.000   0.8540   0.03203   0.02165  -0.0014   0.0965   1.0000
   8.250   0.8641   0.03385   0.02334   0.0002   0.0769   1.0000
   8.500   0.8754   0.03576   0.02527   0.0018   0.0648   1.0000
   8.750   0.8877   0.03772   0.02734   0.0034   0.0565   1.0000
   9.000   0.9024   0.03993   0.02974   0.0049   0.0514   1.0000
   9.250   0.9163   0.04204   0.03206   0.0063   0.0473   1.0000
   9.500   0.9274   0.04423   0.03424   0.0075   0.0441   1.0000
   9.750   0.9394   0.04684   0.03729   0.0089   0.0415   1.0000
  10.000   0.9475   0.04962   0.04041   0.0103   0.0395   1.0000
  10.250   0.9516   0.05250   0.04358   0.0118   0.0386   1.0000
  10.500   0.9511   0.05555   0.04690   0.0134   0.0378   1.0000
  10.750   0.9466   0.05885   0.05044   0.0146   0.0372   1.0000
  11.000   0.9386   0.06246   0.05431   0.0152   0.0369   1.0000
  11.250   0.9264   0.06662   0.05871   0.0150   0.0368   1.0000
  11.500   0.9104   0.07146   0.06378   0.0136   0.0367   1.0000
  11.750   0.8893   0.07753   0.07008   0.0107   0.0370   1.0000
  12.000   0.8634   0.08526   0.07802   0.0058   0.0375   1.0000
  12.250   0.8298   0.09605   0.08899  -0.0018   0.0386   1.0000
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