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EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 266 AIRFOIL (e266-il)
Reynolds number: 500,000
Max Cl/Cd: 100.39 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e266-il-500000.txt
Download as CSV file: xf-e266-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 266 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.2396   0.10960   0.10612  -0.0901   0.7425   0.0237
 -13.000  -0.2428   0.10416   0.10065  -0.0928   0.7367   0.0238
 -12.750  -0.2518   0.09749   0.09399  -0.0955   0.7321   0.0240
 -12.500  -0.2387   0.09806   0.09450  -0.0938   0.7253   0.0246
 -12.250  -0.2370   0.09465   0.09106  -0.0952   0.7207   0.0249
 -12.000  -0.2347   0.09138   0.08778  -0.0966   0.7164   0.0253
 -11.750  -0.2372   0.08705   0.08345  -0.0986   0.7126   0.0257
 -11.500  -0.2235   0.06633   0.06287  -0.1000   0.6999   0.0290
 -11.250  -0.2319   0.06122   0.05774  -0.1023   0.6976   0.0287
 -11.000  -0.2639   0.05383   0.05026  -0.1061   0.6961   0.0286
 -10.750  -0.2730   0.05015   0.04654  -0.1068   0.6937   0.0279
 -10.500  -0.3077   0.04487   0.04111  -0.1072   0.6919   0.0282
 -10.250  -0.3415   0.04119   0.03721  -0.1054   0.6897   0.0286
 -10.000  -0.3749   0.03945   0.03525  -0.1013   0.6876   0.0290
  -9.750  -0.3979   0.03799   0.03364  -0.0967   0.6851   0.0292
  -9.500  -0.4173   0.03642   0.03189  -0.0916   0.6827   0.0293
  -9.250  -0.4286   0.03437   0.02962  -0.0875   0.6804   0.0293
  -9.000  -0.4617   0.03960   0.03441  -0.0885   0.6820   0.0302
  -8.750  -0.4473   0.03775   0.03254  -0.0876   0.6796   0.0307
  -8.500  -0.4362   0.03616   0.03084  -0.0860   0.6774   0.0312
  -8.250  -0.4523   0.02687   0.02011  -0.0775   0.6758   0.0194
  -8.000  -0.4267   0.02429   0.01740  -0.0777   0.6737   0.0185
  -7.750  -0.4036   0.02253   0.01545  -0.0772   0.6718   0.0183
  -7.500  -0.3785   0.02109   0.01385  -0.0769   0.6699   0.0182
  -7.250  -0.3522   0.01988   0.01251  -0.0768   0.6679   0.0181
  -7.000  -0.3268   0.01904   0.01156  -0.0766   0.6658   0.0184
  -6.750  -0.3017   0.01833   0.01076  -0.0763   0.6637   0.0188
  -6.500  -0.2772   0.01779   0.01012  -0.0759   0.6618   0.0191
  -6.250  -0.2527   0.01693   0.00920  -0.0755   0.6600   0.0194
  -6.000  -0.2312   0.01615   0.00838  -0.0747   0.6583   0.0196
  -5.750  -0.2119   0.01552   0.00772  -0.0735   0.6566   0.0201
  -5.500  -0.1923   0.01500   0.00721  -0.0722   0.6552   0.0207
  -5.250  -0.1718   0.01459   0.00679  -0.0712   0.6537   0.0216
  -5.000  -0.1506   0.01422   0.00640  -0.0702   0.6521   0.0224
  -4.750  -0.1284   0.01392   0.00606  -0.0694   0.6504   0.0234
  -4.500  -0.1072   0.01354   0.00565  -0.0684   0.6487   0.0249
  -4.250  -0.0844   0.01325   0.00535  -0.0676   0.6470   0.0275
  -4.000  -0.0616   0.01297   0.00506  -0.0669   0.6454   0.0336
  -3.750  -0.0457   0.01223   0.00469  -0.0651   0.6440   0.1097
  -3.500  -0.0320   0.01142   0.00442  -0.0632   0.6426   0.2417
  -3.250  -0.0217   0.01049   0.00415  -0.0608   0.6411   0.4129
  -3.000  -0.0149   0.00940   0.00388  -0.0573   0.6400   0.6062
  -2.750   0.0053   0.00937   0.00425  -0.0555   0.6386   0.7235
  -2.500   0.0323   0.00961   0.00450  -0.0551   0.6370   0.7496
  -2.250   0.0599   0.00988   0.00474  -0.0549   0.6354   0.7644
  -2.000   0.0879   0.01031   0.00516  -0.0545   0.6340   0.7781
  -1.750   0.1160   0.01084   0.00570  -0.0540   0.6326   0.7904
  -1.500   0.1440   0.01119   0.00600  -0.0538   0.6312   0.7989
  -1.250   0.1723   0.01159   0.00640  -0.0535   0.6298   0.8051
  -1.000   0.2008   0.01198   0.00676  -0.0532   0.6283   0.8107
  -0.750   0.2283   0.01214   0.00683  -0.0533   0.6269   0.8173
  -0.500   0.2564   0.01237   0.00704  -0.0532   0.6256   0.8196
  -0.250   0.2839   0.01255   0.00721  -0.0531   0.6244   0.8220
   0.000   0.3109   0.01263   0.00729  -0.0531   0.6230   0.8245
   0.250   0.3378   0.01265   0.00731  -0.0531   0.6214   0.8272
   0.500   0.3649   0.01265   0.00729  -0.0534   0.6198   0.8304
   0.750   0.3922   0.01263   0.00725  -0.0538   0.6184   0.8332
   1.000   0.4191   0.01264   0.00725  -0.0538   0.6168   0.8345
   1.250   0.4465   0.01266   0.00726  -0.0539   0.6152   0.8359
   1.500   0.4743   0.01269   0.00728  -0.0541   0.6137   0.8373
   1.750   0.5024   0.01273   0.00731  -0.0544   0.6123   0.8387
   2.000   0.5308   0.01279   0.00734  -0.0549   0.6109   0.8403
   2.250   0.5593   0.01295   0.00747  -0.0554   0.6092   0.8419
   2.500   0.5857   0.01293   0.00749  -0.0555   0.6077   0.8439
   2.750   0.6123   0.01293   0.00752  -0.0557   0.6059   0.8457
   3.000   0.6395   0.01293   0.00754  -0.0561   0.6038   0.8474
   3.250   0.6663   0.01291   0.00754  -0.0563   0.6017   0.8489
   3.500   0.6933   0.01287   0.00752  -0.0564   0.5995   0.8499
   3.750   0.7213   0.01283   0.00748  -0.0567   0.5973   0.8509
   4.000   0.7503   0.01284   0.00747  -0.0572   0.5952   0.8518
   4.250   0.7780   0.01293   0.00757  -0.0575   0.5928   0.8529
   4.500   0.8022   0.01290   0.00762  -0.0571   0.5900   0.8544
   4.750   0.8277   0.01286   0.00764  -0.0569   0.5868   0.8559
   5.000   0.8549   0.01280   0.00760  -0.0571   0.5838   0.8573
   5.250   0.8836   0.01274   0.00754  -0.0576   0.5811   0.8585
   5.500   0.9136   0.01275   0.00753  -0.0584   0.5785   0.8597
   5.750   0.9372   0.01271   0.00758  -0.0579   0.5748   0.8613
   6.000   0.9622   0.01262   0.00755  -0.0578   0.5705   0.8627
   6.250   0.9892   0.01249   0.00744  -0.0579   0.5667   0.8640
   6.500   1.0171   0.01242   0.00737  -0.0581   0.5634   0.8651
   6.750   1.0385   0.01235   0.00742  -0.0571   0.5587   0.8664
   7.000   1.0619   0.01224   0.00738  -0.0565   0.5536   0.8676
   7.250   1.0876   0.01211   0.00726  -0.0563   0.5487   0.8689
   7.500   1.1079   0.01204   0.00730  -0.0551   0.5422   0.8704
   7.750   1.1292   0.01187   0.00714  -0.0540   0.5337   0.8720
   8.000   1.1472   0.01179   0.00716  -0.0523   0.5233   0.8738
   8.250   1.1639   0.01172   0.00712  -0.0504   0.5089   0.8758
   8.500   1.1792   0.01175   0.00716  -0.0482   0.4929   0.8779
   8.750   1.1866   0.01182   0.00719  -0.0445   0.4728   0.8798
   9.000   1.1879   0.01208   0.00740  -0.0397   0.4482   0.8820
   9.250   1.1841   0.01265   0.00785  -0.0342   0.4191   0.8846
   9.500   1.1775   0.01343   0.00851  -0.0286   0.3899   0.8876
   9.750   1.1675   0.01446   0.00941  -0.0229   0.3606   0.8909
  10.000   1.1552   0.01575   0.01058  -0.0175   0.3331   0.8943
  10.250   1.1444   0.01715   0.01192  -0.0126   0.3107   0.8977
  10.500   1.1345   0.01881   0.01352  -0.0086   0.2868   0.9011
  10.750   1.1244   0.02075   0.01537  -0.0050   0.2645   0.9046
  11.000   1.1159   0.02280   0.01733  -0.0020   0.2401   0.9079
  11.250   1.1070   0.02490   0.01934   0.0009   0.2168   0.9111
  11.500   1.0991   0.02705   0.02139   0.0034   0.1931   0.9147
  11.750   1.0967   0.02895   0.02322   0.0053   0.1749   0.9184
  12.000   1.0947   0.03087   0.02507   0.0071   0.1559   0.9221
  12.250   1.0909   0.03302   0.02713   0.0087   0.1341   0.9260
  12.500   1.0935   0.03484   0.02890   0.0098   0.1176   0.9299
  12.750   1.0933   0.03692   0.03089   0.0108   0.0985   0.9340
  13.000   1.0963   0.03923   0.03311   0.0108   0.0778   0.9378
  13.250   1.0996   0.04179   0.03555   0.0104   0.0557   0.9418
  13.500   1.1007   0.04483   0.03843   0.0097   0.0340   0.9458
  13.750   1.1091   0.04762   0.04118   0.0081   0.0229   0.9497
  14.000   1.1200   0.05048   0.04406   0.0060   0.0180   0.9534
  14.250   1.1366   0.05291   0.04659   0.0035   0.0168   0.9568
  14.750   1.1563   0.05787   0.05171   0.0011   0.0148   1.0000
  15.000   1.1552   0.06085   0.05475   0.0011   0.0140   1.0000
  15.250   1.1579   0.06348   0.05746   0.0010   0.0138   1.0000
  15.500   1.1645   0.06576   0.05981   0.0008   0.0133   1.0000
  15.750   1.1679   0.06839   0.06252   0.0005   0.0131   1.0000
  16.000   1.1690   0.07132   0.06553   0.0003   0.0125   1.0000
  16.250   1.1733   0.07388   0.06817  -0.0001   0.0123   1.0000
  16.500   1.1739   0.07693   0.07129  -0.0004   0.0122   1.0000
  16.750   1.1736   0.08012   0.07454  -0.0008   0.0119   1.0000
  17.000   1.1738   0.08326   0.07775  -0.0013   0.0117   1.0000
  17.250   1.1715   0.08674   0.08130  -0.0019   0.0114   1.0000
  17.500   1.1710   0.08998   0.08460  -0.0024   0.0113   1.0000
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