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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 500,000
Max Cl/Cd: 89.8 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e222-il-500000-n5.txt
Download as CSV file: xf-e222-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5004   0.08714   0.08480  -0.0369   1.0000   0.0096
 -10.250  -0.5232   0.07857   0.07628  -0.0404   1.0000   0.0095
 -10.000  -0.6152   0.05255   0.05017  -0.0563   1.0000   0.0090
  -9.750  -0.6489   0.04665   0.04419  -0.0598   1.0000   0.0089
  -9.500  -0.6747   0.04254   0.03991  -0.0596   0.9998   0.0088
  -9.250  -0.6648   0.03568   0.03253  -0.0669   0.9950   0.0090
  -9.000  -0.6487   0.03128   0.02768  -0.0701   0.9910   0.0091
  -8.750  -0.6270   0.02803   0.02404  -0.0723   0.9874   0.0092
  -8.500  -0.6005   0.02560   0.02126  -0.0743   0.9850   0.0095
  -8.250  -0.5707   0.02400   0.01938  -0.0762   0.9833   0.0098
  -8.000  -0.5478   0.02248   0.01762  -0.0763   0.9786   0.0100
  -7.750  -0.5200   0.02093   0.01582  -0.0773   0.9754   0.0101
  -7.500  -0.4899   0.01960   0.01428  -0.0785   0.9730   0.0102
  -7.000  -0.4359   0.01650   0.01080  -0.0797   0.9659   0.0106
  -6.750  -0.4076   0.01526   0.00944  -0.0804   0.9623   0.0110
  -6.500  -0.3763   0.01440   0.00850  -0.0815   0.9597   0.0113
  -6.250  -0.3436   0.01366   0.00768  -0.0829   0.9578   0.0117
  -6.000  -0.3179   0.01305   0.00701  -0.0827   0.9516   0.0120
  -5.750  -0.2865   0.01245   0.00635  -0.0837   0.9478   0.0124
  -5.500  -0.2531   0.01188   0.00570  -0.0850   0.9448   0.0128
  -5.250  -0.2241   0.01141   0.00518  -0.0854   0.9387   0.0133
  -5.000  -0.1919   0.01099   0.00470  -0.0864   0.9337   0.0140
  -4.750  -0.1583   0.01058   0.00422  -0.0877   0.9292   0.0145
  -4.500  -0.1283   0.01023   0.00379  -0.0882   0.9216   0.0148
  -4.250  -0.0950   0.00983   0.00331  -0.0894   0.9155   0.0158
  -4.000  -0.0653   0.00954   0.00297  -0.0898   0.9064   0.0171
  -3.750  -0.0345   0.00929   0.00267  -0.0903   0.8976   0.0192
  -3.500  -0.0043   0.00902   0.00239  -0.0908   0.8878   0.0279
  -3.250   0.0237   0.00861   0.00214  -0.0910   0.8766   0.0738
  -3.000   0.0517   0.00824   0.00194  -0.0912   0.8651   0.1266
  -2.750   0.0797   0.00798   0.00178  -0.0913   0.8532   0.1705
  -2.500   0.1072   0.00771   0.00165  -0.0914   0.8407   0.2250
  -2.250   0.1346   0.00749   0.00155  -0.0914   0.8276   0.2766
  -2.000   0.1617   0.00728   0.00147  -0.0913   0.8143   0.3326
  -1.750   0.1886   0.00708   0.00141  -0.0912   0.8004   0.3953
  -1.500   0.2156   0.00695   0.00137  -0.0910   0.7862   0.4429
  -1.250   0.2426   0.00689   0.00134  -0.0908   0.7717   0.4756
  -1.000   0.2696   0.00684   0.00131  -0.0906   0.7566   0.5087
  -0.750   0.2964   0.00681   0.00130  -0.0903   0.7411   0.5402
  -0.500   0.3232   0.00679   0.00131  -0.0900   0.7252   0.5704
  -0.250   0.3498   0.00679   0.00132  -0.0897   0.7089   0.5998
   0.000   0.3764   0.00679   0.00134  -0.0893   0.6923   0.6292
   0.250   0.4028   0.00681   0.00138  -0.0889   0.6755   0.6576
   0.500   0.4290   0.00685   0.00142  -0.0885   0.6582   0.6847
   0.750   0.4552   0.00690   0.00147  -0.0881   0.6403   0.7106
   1.000   0.4811   0.00696   0.00153  -0.0876   0.6215   0.7354
   1.250   0.5068   0.00703   0.00161  -0.0870   0.6027   0.7600
   1.500   0.5322   0.00712   0.00169  -0.0864   0.5840   0.7850
   1.750   0.5573   0.00719   0.00178  -0.0857   0.5649   0.8095
   2.000   0.5820   0.00730   0.00188  -0.0849   0.5449   0.8327
   2.250   0.6063   0.00741   0.00199  -0.0841   0.5248   0.8551
   2.500   0.6298   0.00754   0.00209  -0.0830   0.5034   0.8773
   2.750   0.6527   0.00768   0.00220  -0.0819   0.4819   0.9008
   3.000   0.6749   0.00780   0.00230  -0.0805   0.4597   0.9263
   3.500   0.7314   0.00817   0.00253  -0.0808   0.4099   1.0000
   3.750   0.7570   0.00843   0.00269  -0.0804   0.3848   1.0000
   4.000   0.7823   0.00872   0.00287  -0.0800   0.3579   1.0000
   4.250   0.8077   0.00901   0.00308  -0.0797   0.3336   1.0000
   4.500   0.8327   0.00933   0.00330  -0.0793   0.3077   1.0000
   4.750   0.8575   0.00968   0.00353  -0.0788   0.2810   1.0000
   5.000   0.8810   0.01013   0.00381  -0.0782   0.2431   1.0000
   5.250   0.9035   0.01070   0.00416  -0.0775   0.1993   1.0000
   5.500   0.9269   0.01119   0.00449  -0.0768   0.1673   1.0000
   5.750   0.9503   0.01165   0.00484  -0.0762   0.1409   1.0000
   6.000   0.9733   0.01216   0.00521  -0.0755   0.1143   1.0000
   6.250   0.9961   0.01269   0.00561  -0.0748   0.0903   1.0000
   6.500   1.0185   0.01323   0.00606  -0.0740   0.0683   1.0000
   6.750   1.0401   0.01385   0.00654  -0.0732   0.0465   1.0000
   7.000   1.0619   0.01443   0.00704  -0.0723   0.0319   1.0000
   7.250   1.0826   0.01512   0.00764  -0.0712   0.0158   1.0000
   7.500   1.1036   0.01577   0.00826  -0.0702   0.0099   1.0000
   7.750   1.1255   0.01630   0.00885  -0.0693   0.0085   1.0000
   8.000   1.1473   0.01682   0.00944  -0.0683   0.0078   1.0000
   8.250   1.1682   0.01741   0.01008  -0.0673   0.0071   1.0000
   8.500   1.1880   0.01808   0.01082  -0.0661   0.0064   1.0000
   8.750   1.2063   0.01887   0.01170  -0.0647   0.0059   1.0000
   9.000   1.2253   0.01952   0.01243  -0.0634   0.0058   1.0000
   9.250   1.2433   0.02023   0.01323  -0.0619   0.0056   1.0000
   9.500   1.2601   0.02099   0.01409  -0.0604   0.0055   1.0000
   9.750   1.2746   0.02179   0.01499  -0.0584   0.0053   1.0000
  10.000   1.2871   0.02264   0.01592  -0.0561   0.0051   1.0000
  10.250   1.2982   0.02355   0.01693  -0.0537   0.0050   1.0000
  10.500   1.3082   0.02454   0.01802  -0.0512   0.0049   1.0000
  10.750   1.3170   0.02561   0.01918  -0.0488   0.0048   1.0000
  11.000   1.3246   0.02678   0.02046  -0.0463   0.0046   1.0000
  11.250   1.3313   0.02805   0.02183  -0.0439   0.0045   1.0000
  11.500   1.3366   0.02946   0.02337  -0.0416   0.0045   1.0000
  11.750   1.3409   0.03100   0.02502  -0.0394   0.0044   1.0000
  12.000   1.3445   0.03267   0.02681  -0.0374   0.0043   1.0000
  12.250   1.3466   0.03456   0.02881  -0.0355   0.0042   1.0000
  12.500   1.3477   0.03664   0.03102  -0.0339   0.0042   1.0000
  12.750   1.3471   0.03900   0.03350  -0.0325   0.0041   1.0000
  13.000   1.3462   0.04155   0.03619  -0.0315   0.0041   1.0000
  13.250   1.3437   0.04441   0.03918  -0.0308   0.0040   1.0000
  13.500   1.3400   0.04759   0.04250  -0.0304   0.0040   1.0000
  13.750   1.3354   0.05104   0.04610  -0.0304   0.0040   1.0000
  14.000   1.3298   0.05484   0.05004  -0.0308   0.0039   1.0000
  14.250   1.3216   0.05919   0.05454  -0.0317   0.0039   1.0000
  14.500   1.3126   0.06391   0.05942  -0.0331   0.0038   1.0000
  14.750   1.3033   0.06896   0.06463  -0.0348   0.0038   1.0000
  15.000   1.2916   0.07464   0.07048  -0.0371   0.0038   1.0000
  15.250   1.2804   0.08057   0.07657  -0.0398   0.0038   1.0000
  15.500   1.2684   0.08693   0.08309  -0.0430   0.0038   1.0000
  15.750   1.2537   0.09407   0.09041  -0.0467   0.0037   1.0000
  16.000   1.2400   0.10135   0.09784  -0.0507   0.0037   1.0000
  16.250   1.2279   0.10859   0.10523  -0.0548   0.0037   1.0000
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