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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 200,000
Max Cl/Cd: 41.58 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e230-il-200000.txt
Download as CSV file: xf-e230-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.9873   0.04543   0.03984   0.0101   1.0000   0.0284
  -9.000  -0.9762   0.04096   0.03516   0.0113   1.0000   0.0272
  -8.750  -0.9678   0.03690   0.03072   0.0132   1.0000   0.0264
  -8.500  -0.9550   0.03346   0.02688   0.0150   1.0000   0.0257
  -8.250  -0.9381   0.03051   0.02354   0.0165   1.0000   0.0253
  -8.000  -0.9180   0.02802   0.02074   0.0177   1.0000   0.0252
  -7.750  -0.8959   0.02593   0.01840   0.0187   1.0000   0.0253
  -7.500  -0.8731   0.02413   0.01643   0.0196   1.0000   0.0259
  -7.250  -0.8504   0.02257   0.01474   0.0205   1.0000   0.0267
  -7.000  -0.8280   0.02125   0.01331   0.0215   1.0000   0.0275
  -6.750  -0.8085   0.01968   0.01170   0.0228   1.0000   0.0295
  -6.500  -0.7879   0.01859   0.01060   0.0238   1.0000   0.0326
  -6.250  -0.7665   0.01760   0.00952   0.0250   1.0000   0.0356
  -6.000  -0.7471   0.01637   0.00827   0.0265   1.0000   0.0418
  -5.750  -0.7310   0.01460   0.00689   0.0284   1.0000   0.0967
  -5.500  -0.7110   0.01357   0.00627   0.0294   1.0000   0.1686
  -5.250  -0.6892   0.01289   0.00583   0.0302   1.0000   0.2238
  -5.000  -0.6673   0.01230   0.00546   0.0310   1.0000   0.2765
  -4.750  -0.6459   0.01175   0.00515   0.0319   1.0000   0.3307
  -4.500  -0.6249   0.01127   0.00489   0.0331   1.0000   0.3850
  -4.250  -0.6042   0.01084   0.00462   0.0343   1.0000   0.4309
  -4.000  -0.5846   0.01046   0.00441   0.0358   1.0000   0.4742
  -3.750  -0.5675   0.01013   0.00423   0.0378   1.0000   0.5169
  -3.500  -0.5523   0.00983   0.00409   0.0402   1.0000   0.5573
  -3.250  -0.5378   0.00958   0.00399   0.0427   1.0000   0.5982
  -3.000  -0.5232   0.00937   0.00392   0.0452   1.0000   0.6396
  -2.750  -0.4920   0.00918   0.00391   0.0444   0.9942   0.6882
  -2.500  -0.4494   0.00905   0.00392   0.0415   0.9856   0.7376
  -2.250  -0.4057   0.00897   0.00395   0.0386   0.9775   0.7800
  -2.000  -0.3597   0.00896   0.00402   0.0353   0.9702   0.8166
  -1.750  -0.3146   0.00902   0.00411   0.0323   0.9612   0.8465
  -1.500  -0.2722   0.00914   0.00422   0.0300   0.9501   0.8712
  -1.250  -0.2300   0.00933   0.00439   0.0278   0.9380   0.8892
  -1.000  -0.1924   0.00953   0.00455   0.0266   0.9235   0.9041
  -0.750  -0.1583   0.00975   0.00472   0.0262   0.9075   0.9174
  -0.500  -0.1202   0.00997   0.00489   0.0250   0.8916   0.9270
  -0.250  -0.0825   0.01016   0.00502   0.0237   0.8750   0.9359
   0.000  -0.0480   0.01031   0.00511   0.0230   0.8573   0.9467
   0.250  -0.0101   0.01044   0.00518   0.0214   0.8379   0.9564
   0.500   0.0299   0.01050   0.00519   0.0194   0.8179   0.9645
   0.750   0.0677   0.01053   0.00516   0.0177   0.7972   0.9741
   1.000   0.1079   0.01051   0.00509   0.0153   0.7737   0.9829
   1.250   0.1504   0.01039   0.00490   0.0124   0.7488   0.9902
   1.500   0.1925   0.01024   0.00468   0.0096   0.7219   0.9978
   1.750   0.2199   0.01015   0.00452   0.0095   0.6956   1.0000
   2.000   0.2411   0.01011   0.00441   0.0106   0.6689   1.0000
   2.250   0.2628   0.01010   0.00433   0.0117   0.6417   1.0000
   2.500   0.2850   0.01013   0.00427   0.0127   0.6132   1.0000
   2.750   0.3076   0.01018   0.00425   0.0137   0.5834   1.0000
   3.000   0.3306   0.01026   0.00425   0.0146   0.5524   1.0000
   3.250   0.3539   0.01037   0.00428   0.0154   0.5199   1.0000
   3.500   0.3773   0.01052   0.00433   0.0161   0.4854   1.0000
   3.750   0.4011   0.01069   0.00443   0.0168   0.4471   1.0000
   4.000   0.4249   0.01091   0.00455   0.0174   0.4083   1.0000
   4.250   0.4488   0.01118   0.00469   0.0180   0.3639   1.0000
   4.500   0.4725   0.01153   0.00489   0.0185   0.3127   1.0000
   4.750   0.4961   0.01196   0.00512   0.0190   0.2603   1.0000
   5.000   0.5193   0.01249   0.00542   0.0194   0.2061   1.0000
   5.250   0.5424   0.01306   0.00580   0.0198   0.1563   1.0000
   5.500   0.5649   0.01382   0.00633   0.0203   0.1035   1.0000
   5.750   0.5854   0.01539   0.00755   0.0211   0.0494   1.0000
   6.000   0.6064   0.01648   0.00867   0.0222   0.0416   1.0000
   6.250   0.6271   0.01740   0.00959   0.0231   0.0372   1.0000
   6.500   0.6466   0.01861   0.01084   0.0244   0.0343   1.0000
   6.750   0.6670   0.01967   0.01201   0.0256   0.0328   1.0000
   7.000   0.6872   0.02087   0.01330   0.0269   0.0316   1.0000
   7.250   0.7073   0.02221   0.01474   0.0283   0.0307   1.0000
   7.500   0.7272   0.02371   0.01637   0.0296   0.0300   1.0000
   7.750   0.7466   0.02547   0.01831   0.0309   0.0297   1.0000
   8.000   0.7648   0.02755   0.02065   0.0324   0.0296   1.0000
   8.250   0.7808   0.03014   0.02361   0.0340   0.0300   1.0000
   8.500   0.7946   0.03261   0.02641   0.0356   0.0298   1.0000
   8.750   0.8076   0.03484   0.02886   0.0371   0.0292   1.0000
   9.000   0.8167   0.03754   0.03185   0.0388   0.0289   1.0000
   9.250   0.8024   0.04378   0.03893   0.0420   0.0311   1.0000
   9.500   0.7911   0.04856   0.04407   0.0440   0.0327   1.0000
   9.750   0.7784   0.05276   0.04849   0.0457   0.0337   1.0000
  10.000   0.7633   0.05695   0.05279   0.0471   0.0347   1.0000
  10.250   0.6696   0.04673   0.04291   0.0500   0.0335   1.0000
  10.500   0.6433   0.05212   0.04842   0.0477   0.0338   1.0000
  10.750   0.6154   0.05917   0.05556   0.0437   0.0341   1.0000
  11.000   0.5917   0.06710   0.06352   0.0400   0.0350   1.0000
  11.250   0.5806   0.11319   0.10942   0.0128   0.0648   1.0000
  11.500   0.5806   0.11727   0.11348   0.0111   0.0619   1.0000
  11.750   0.5897   0.11956   0.11578   0.0116   0.0593   1.0000
  12.000   0.5975   0.12252   0.11874   0.0119   0.0584   1.0000
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