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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.24 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e222-il-1000000.txt
Download as CSV file: xf-e222-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E222  (10.17%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3808   0.08188   0.08036  -0.0376   1.0000   0.0143
 -10.000  -0.3868   0.07741   0.07590  -0.0383   1.0000   0.0146
  -9.750  -0.3950   0.07251   0.07103  -0.0391   1.0000   0.0148
  -9.500  -0.4086   0.06663   0.06517  -0.0404   1.0000   0.0149
  -9.250  -0.4326   0.05868   0.05726  -0.0424   1.0000   0.0148
  -8.000  -0.5422   0.02317   0.01958  -0.0781   0.9853   0.0122
  -7.750  -0.5119   0.02059   0.01666  -0.0801   0.9842   0.0122
  -7.500  -0.4866   0.01863   0.01445  -0.0805   0.9808   0.0122
  -7.250  -0.4584   0.01703   0.01265  -0.0813   0.9778   0.0122
  -7.000  -0.4273   0.01564   0.01108  -0.0825   0.9758   0.0123
  -6.750  -0.3948   0.01447   0.00977  -0.0838   0.9742   0.0124
  -6.500  -0.3607   0.01373   0.00893  -0.0854   0.9730   0.0127
  -6.250  -0.3259   0.01301   0.00813  -0.0871   0.9720   0.0130
  -6.000  -0.2910   0.01216   0.00720  -0.0888   0.9711   0.0132
  -5.750  -0.2685   0.01081   0.00575  -0.0880   0.9647   0.0137
  -5.500  -0.2362   0.01003   0.00490  -0.0892   0.9620   0.0143
  -5.250  -0.2029   0.00948   0.00430  -0.0905   0.9596   0.0148
  -5.000  -0.1715   0.00905   0.00382  -0.0913   0.9559   0.0153
  -4.750  -0.1432   0.00867   0.00340  -0.0914   0.9494   0.0158
  -4.500  -0.1102   0.00832   0.00299  -0.0925   0.9452   0.0165
  -4.250  -0.0811   0.00804   0.00268  -0.0927   0.9377   0.0174
  -4.000  -0.0494   0.00775   0.00232  -0.0934   0.9311   0.0188
  -3.750  -0.0206   0.00750   0.00204  -0.0935   0.9218   0.0225
  -3.500   0.0082   0.00701   0.00173  -0.0938   0.9126   0.0712
  -3.250   0.0361   0.00660   0.00153  -0.0940   0.9021   0.1343
  -3.000   0.0634   0.00631   0.00139  -0.0940   0.8907   0.1866
  -2.750   0.0907   0.00603   0.00127  -0.0940   0.8792   0.2465
  -2.500   0.1181   0.00582   0.00118  -0.0940   0.8674   0.2970
  -2.250   0.1455   0.00568   0.00111  -0.0939   0.8552   0.3391
  -2.000   0.1727   0.00555   0.00105  -0.0937   0.8423   0.3824
  -1.750   0.1996   0.00538   0.00101  -0.0936   0.8289   0.4417
  -1.500   0.2265   0.00525   0.00099  -0.0934   0.8149   0.4939
  -1.250   0.2536   0.00520   0.00097  -0.0931   0.8007   0.5293
  -1.000   0.2807   0.00516   0.00095  -0.0929   0.7861   0.5593
  -0.750   0.3078   0.00514   0.00095  -0.0927   0.7713   0.5906
  -0.500   0.3347   0.00512   0.00096  -0.0924   0.7561   0.6215
  -0.250   0.3617   0.00512   0.00097  -0.0921   0.7405   0.6509
   0.000   0.3885   0.00513   0.00099  -0.0919   0.7242   0.6788
   0.250   0.4153   0.00514   0.00103  -0.0915   0.7074   0.7058
   0.500   0.4419   0.00517   0.00107  -0.0912   0.6901   0.7319
   0.750   0.4684   0.00521   0.00111  -0.0908   0.6728   0.7570
   1.000   0.4948   0.00527   0.00116  -0.0904   0.6554   0.7815
   1.250   0.5209   0.00533   0.00122  -0.0899   0.6374   0.8043
   1.500   0.5470   0.00540   0.00129  -0.0895   0.6186   0.8267
   1.750   0.5726   0.00548   0.00137  -0.0889   0.5989   0.8478
   2.000   0.5977   0.00558   0.00145  -0.0882   0.5788   0.8694
   2.250   0.6224   0.00567   0.00153  -0.0874   0.5585   0.8905
   2.500   0.6459   0.00579   0.00162  -0.0863   0.5370   0.9123
   2.750   0.6686   0.00588   0.00169  -0.0851   0.5159   0.9348
   3.000   0.6915   0.00599   0.00176  -0.0839   0.4935   0.9624
   3.250   0.7242   0.00615   0.00184  -0.0850   0.4672   1.0000
   3.500   0.7508   0.00635   0.00196  -0.0849   0.4437   1.0000
   3.750   0.7771   0.00659   0.00209  -0.0846   0.4183   1.0000
   4.000   0.8032   0.00683   0.00223  -0.0844   0.3927   1.0000
   4.250   0.8289   0.00711   0.00240  -0.0840   0.3644   1.0000
   4.500   0.8539   0.00745   0.00259  -0.0836   0.3295   1.0000
   4.750   0.8786   0.00782   0.00280  -0.0831   0.2937   1.0000
   5.000   0.9029   0.00822   0.00304  -0.0826   0.2580   1.0000
   5.250   0.9269   0.00865   0.00330  -0.0820   0.2214   1.0000
   5.500   0.9508   0.00909   0.00357  -0.0815   0.1892   1.0000
   5.750   0.9748   0.00952   0.00386  -0.0809   0.1598   1.0000
   6.000   0.9983   0.00998   0.00419  -0.0803   0.1311   1.0000
   6.250   1.0217   0.01045   0.00453  -0.0796   0.1051   1.0000
   6.500   1.0447   0.01096   0.00490  -0.0789   0.0811   1.0000
   6.750   1.0672   0.01150   0.00531  -0.0781   0.0585   1.0000
   7.000   1.0888   0.01213   0.00579  -0.0772   0.0352   1.0000
   7.250   1.1078   0.01302   0.00650  -0.0758   0.0120   1.0000
   7.500   1.1307   0.01351   0.00700  -0.0750   0.0096   1.0000
   7.750   1.1529   0.01406   0.00759  -0.0740   0.0083   1.0000
   8.000   1.1750   0.01460   0.00819  -0.0731   0.0078   1.0000
   8.250   1.1973   0.01508   0.00873  -0.0722   0.0075   1.0000
   8.500   1.2188   0.01563   0.00934  -0.0712   0.0072   1.0000
   8.750   1.2397   0.01621   0.00998  -0.0701   0.0070   1.0000
   9.000   1.2598   0.01683   0.01066  -0.0689   0.0067   1.0000
   9.250   1.2788   0.01751   0.01139  -0.0676   0.0064   1.0000
   9.500   1.2965   0.01827   0.01222  -0.0660   0.0062   1.0000
   9.750   1.3115   0.01919   0.01322  -0.0641   0.0060   1.0000
  10.000   1.3200   0.02053   0.01469  -0.0612   0.0057   1.0000
  10.250   1.3205   0.02211   0.01641  -0.0569   0.0055   1.0000
  10.500   1.3314   0.02297   0.01735  -0.0544   0.0055   1.0000
  10.750   1.3411   0.02393   0.01839  -0.0518   0.0054   1.0000
  11.000   1.3497   0.02498   0.01954  -0.0492   0.0054   1.0000
  11.250   1.3564   0.02620   0.02086  -0.0466   0.0053   1.0000
  11.500   1.3619   0.02757   0.02233  -0.0440   0.0053   1.0000
  11.750   1.3671   0.02901   0.02387  -0.0416   0.0052   1.0000
  12.000   1.3733   0.03039   0.02535  -0.0395   0.0051   1.0000
  12.250   1.3773   0.03203   0.02710  -0.0374   0.0050   1.0000
  12.500   1.3789   0.03398   0.02917  -0.0354   0.0050   1.0000
  12.750   1.3803   0.03604   0.03137  -0.0337   0.0049   1.0000
  13.000   1.3811   0.03825   0.03370  -0.0322   0.0049   1.0000
  13.250   1.3789   0.04092   0.03651  -0.0310   0.0049   1.0000
  13.500   1.3760   0.04379   0.03952  -0.0300   0.0048   1.0000
  13.750   1.3706   0.04715   0.04303  -0.0294   0.0048   1.0000
  14.000   1.3656   0.05058   0.04661  -0.0293   0.0048   1.0000
  14.250   1.3582   0.05456   0.05075  -0.0296   0.0048   1.0000
  14.500   1.3503   0.05880   0.05513  -0.0304   0.0048   1.0000
  14.750   1.3391   0.06380   0.06031  -0.0318   0.0048   1.0000
  15.000   1.3277   0.06913   0.06580  -0.0337   0.0048   1.0000
  15.250   1.3158   0.07486   0.07168  -0.0361   0.0048   1.0000
  15.500   1.3008   0.08149   0.07849  -0.0393   0.0048   1.0000
  15.750   1.2870   0.08828   0.08543  -0.0428   0.0048   1.0000
  16.000   1.2701   0.09602   0.09333  -0.0471   0.0049   1.0000
  16.250   1.2524   0.10437   0.10184  -0.0520   0.0049   1.0000
  16.500   1.2340   0.11324   0.11087  -0.0573   0.0050   1.0000
  16.750   1.2162   0.12235   0.12012  -0.0629   0.0050   1.0000
  17.000   1.1970   0.13218   0.13010  -0.0690   0.0050   1.0000
  17.250   1.1776   0.14245   0.14051  -0.0755   0.0051   1.0000
  17.500   1.1561   0.15371   0.15191  -0.0826   0.0051   1.0000
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