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EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1213 AIRFOIL (e1213-il)
Reynolds number: 500,000
Max Cl/Cd: 80.23 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1213-il-500000-n5.txt
Download as CSV file: xf-e1213-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1213 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.9353   0.08553   0.08091  -0.0250   1.0000   0.0210
 -16.000  -0.9484   0.08017   0.07548  -0.0277   1.0000   0.0211
 -15.750  -0.9656   0.07445   0.06968  -0.0306   1.0000   0.0212
 -15.500  -0.9884   0.06824   0.06337  -0.0338   1.0000   0.0213
 -15.250  -1.0116   0.06207   0.05709  -0.0369   1.0000   0.0213
 -15.000  -1.0390   0.05536   0.05025  -0.0403   1.0000   0.0213
 -14.750  -1.0664   0.04855   0.04330  -0.0439   1.0000   0.0214
 -14.500  -1.0881   0.04223   0.03683  -0.0475   1.0000   0.0213
 -14.250  -1.1057   0.03636   0.03079  -0.0512   1.0000   0.0214
 -14.000  -1.1180   0.03178   0.02607  -0.0540   1.0000   0.0217
 -13.750  -1.1251   0.02874   0.02291  -0.0547   1.0000   0.0219
 -13.500  -1.1281   0.02671   0.02078  -0.0539   1.0000   0.0222
 -13.250  -1.1284   0.02523   0.01923  -0.0521   1.0000   0.0226
 -13.000  -1.1256   0.02413   0.01806  -0.0498   1.0000   0.0229
 -12.750  -1.1216   0.02322   0.01709  -0.0470   1.0000   0.0235
 -12.500  -1.1138   0.02239   0.01620  -0.0445   1.0000   0.0241
 -12.250  -1.1027   0.02153   0.01531  -0.0425   1.0000   0.0249
 -12.000  -1.0891   0.02077   0.01451  -0.0408   1.0000   0.0260
 -11.750  -1.0735   0.02008   0.01379  -0.0391   1.0000   0.0273
 -11.500  -1.0583   0.01933   0.01302  -0.0375   1.0000   0.0296
 -11.250  -1.0420   0.01863   0.01232  -0.0359   1.0000   0.0325
 -11.000  -1.0257   0.01791   0.01161  -0.0342   1.0000   0.0376
 -10.750  -1.0059   0.01720   0.01092  -0.0332   0.9975   0.0444
 -10.500  -0.9697   0.01629   0.01006  -0.0356   0.9525   0.0555
 -10.250  -0.9247   0.01547   0.00918  -0.0395   0.8808   0.0690
 -10.000  -0.9049   0.01504   0.00863  -0.0380   0.8324   0.0788
  -9.750  -0.8841   0.01465   0.00816  -0.0367   0.7999   0.0882
  -9.500  -0.8619   0.01429   0.00773  -0.0357   0.7738   0.0974
  -9.250  -0.8386   0.01398   0.00736  -0.0348   0.7511   0.1056
  -9.000  -0.8145   0.01370   0.00701  -0.0340   0.7306   0.1135
  -8.750  -0.7901   0.01342   0.00669  -0.0332   0.7121   0.1213
  -8.500  -0.7651   0.01316   0.00639  -0.0325   0.6948   0.1294
  -8.250  -0.7395   0.01296   0.00612  -0.0320   0.6789   0.1373
  -8.000  -0.7140   0.01273   0.00587  -0.0314   0.6637   0.1452
  -7.750  -0.6876   0.01256   0.00565  -0.0309   0.6487   0.1517
  -7.500  -0.6613   0.01239   0.00544  -0.0304   0.6351   0.1583
  -7.250  -0.6343   0.01227   0.00525  -0.0299   0.6217   0.1640
  -7.000  -0.6077   0.01211   0.00507  -0.0295   0.6087   0.1698
  -6.750  -0.5804   0.01200   0.00490  -0.0291   0.5967   0.1757
  -6.500  -0.5533   0.01189   0.00474  -0.0287   0.5844   0.1810
  -6.250  -0.5259   0.01178   0.00460  -0.0284   0.5729   0.1867
  -6.000  -0.4982   0.01172   0.00446  -0.0280   0.5620   0.1913
  -5.750  -0.4708   0.01161   0.00432  -0.0277   0.5504   0.1954
  -5.500  -0.4432   0.01151   0.00418  -0.0273   0.5404   0.1992
  -5.250  -0.4155   0.01144   0.00406  -0.0270   0.5298   0.2029
  -5.000  -0.3875   0.01138   0.00393  -0.0267   0.5198   0.2061
  -4.750  -0.3596   0.01132   0.00380  -0.0264   0.5096   0.2089
  -4.500  -0.3319   0.01122   0.00369  -0.0261   0.5008   0.2126
  -4.250  -0.3041   0.01116   0.00358  -0.0258   0.4908   0.2160
  -4.000  -0.2760   0.01111   0.00349  -0.0255   0.4819   0.2193
  -3.750  -0.2478   0.01107   0.00339  -0.0253   0.4729   0.2224
  -3.500  -0.2198   0.01103   0.00330  -0.0250   0.4645   0.2253
  -3.250  -0.1919   0.01096   0.00321  -0.0247   0.4553   0.2286
  -3.000  -0.1640   0.01092   0.00313  -0.0244   0.4472   0.2321
  -2.750  -0.1357   0.01088   0.00307  -0.0242   0.4393   0.2358
  -2.250  -0.0792   0.01085   0.00294  -0.0237   0.4230   0.2414
  -2.000  -0.0514   0.01080   0.00288  -0.0234   0.4151   0.2454
  -1.750  -0.0234   0.01078   0.00285  -0.0232   0.4083   0.2494
  -1.500   0.0049   0.01076   0.00281  -0.0230   0.4004   0.2531
  -1.250   0.0329   0.01078   0.00277  -0.0227   0.3928   0.2565
  -1.000   0.0613   0.01077   0.00275  -0.0225   0.3860   0.2601
  -0.750   0.0891   0.01075   0.00272  -0.0223   0.3787   0.2647
  -0.500   0.1172   0.01075   0.00272  -0.0220   0.3718   0.2691
  -0.250   0.1454   0.01076   0.00271  -0.0218   0.3647   0.2734
   0.000   0.1733   0.01081   0.00271  -0.0216   0.3577   0.2777
   0.250   0.2013   0.01079   0.00271  -0.0213   0.3513   0.2836
   0.500   0.2293   0.01081   0.00273  -0.0211   0.3442   0.2894
   0.750   0.2572   0.01086   0.00275  -0.0209   0.3378   0.2947
   1.000   0.2852   0.01086   0.00278  -0.0206   0.3314   0.3010
   1.250   0.3129   0.01090   0.00281  -0.0204   0.3249   0.3089
   1.500   0.3406   0.01094   0.00286  -0.0201   0.3197   0.3170
   1.750   0.3685   0.01095   0.00291  -0.0199   0.3140   0.3269
   2.000   0.3961   0.01101   0.00296  -0.0196   0.3077   0.3362
   2.250   0.4235   0.01105   0.00303  -0.0194   0.3022   0.3480
   2.500   0.4512   0.01108   0.00310  -0.0191   0.2969   0.3606
   2.750   0.4785   0.01113   0.00318  -0.0188   0.2916   0.3760
   3.000   0.5055   0.01119   0.00328  -0.0185   0.2867   0.3949
   3.250   0.5329   0.01120   0.00337  -0.0182   0.2821   0.4158
   3.500   0.5599   0.01123   0.00347  -0.0179   0.2766   0.4386
   3.750   0.5863   0.01130   0.00359  -0.0175   0.2711   0.4647
   4.250   0.6396   0.01132   0.00384  -0.0168   0.2624   0.5321
   4.500   0.6653   0.01134   0.00398  -0.0162   0.2578   0.5759
   4.750   0.6903   0.01136   0.00414  -0.0156   0.2536   0.6247
   5.000   0.7156   0.01133   0.00430  -0.0149   0.2497   0.6771
   5.250   0.7397   0.01130   0.00446  -0.0140   0.2452   0.7364
   5.500   0.7620   0.01126   0.00464  -0.0127   0.2406   0.8101
   5.750   0.7933   0.01125   0.00490  -0.0130   0.2364   0.9104
   6.000   0.8522   0.01148   0.00516  -0.0192   0.2312   0.9695
   6.250   0.8886   0.01171   0.00537  -0.0210   0.2266   0.9862
   6.500   0.9236   0.01199   0.00560  -0.0225   0.2224   0.9965
   6.750   0.9546   0.01218   0.00580  -0.0231   0.2190   1.0000
   7.000   0.9778   0.01239   0.00600  -0.0222   0.2153   1.0000
   7.250   1.0005   0.01263   0.00622  -0.0211   0.2115   1.0000
   7.500   1.0226   0.01291   0.00647  -0.0201   0.2081   1.0000
   7.750   1.0455   0.01313   0.00670  -0.0191   0.2055   1.0000
   8.000   1.0685   0.01335   0.00694  -0.0182   0.2028   1.0000
   8.250   1.0911   0.01360   0.00719  -0.0172   0.1999   1.0000
   8.500   1.1131   0.01388   0.00747  -0.0161   0.1969   1.0000
   8.750   1.1344   0.01421   0.00777  -0.0150   0.1939   1.0000
   9.000   1.1563   0.01449   0.00807  -0.0140   0.1914   1.0000
   9.250   1.1786   0.01475   0.00836  -0.0131   0.1889   1.0000
   9.500   1.2003   0.01504   0.00867  -0.0120   0.1865   1.0000
   9.750   1.2212   0.01537   0.00900  -0.0109   0.1841   1.0000
  10.000   1.2411   0.01573   0.00937  -0.0097   0.1817   1.0000
  10.250   1.2597   0.01614   0.00977  -0.0084   0.1792   1.0000
  10.500   1.2795   0.01647   0.01014  -0.0071   0.1772   1.0000
  10.750   1.2990   0.01680   0.01052  -0.0059   0.1753   1.0000
  11.000   1.3170   0.01717   0.01092  -0.0045   0.1733   1.0000
  11.250   1.3317   0.01757   0.01135  -0.0025   0.1713   1.0000
  11.500   1.3442   0.01804   0.01184  -0.0003   0.1691   1.0000
  11.750   1.3555   0.01859   0.01240   0.0019   0.1670   1.0000
  12.000   1.3654   0.01925   0.01307   0.0040   0.1649   1.0000
  12.250   1.3801   0.01977   0.01366   0.0055   0.1634   1.0000
  12.500   1.3935   0.02040   0.01435   0.0069   0.1617   1.0000
  12.750   1.4056   0.02115   0.01515   0.0082   0.1596   1.0000
  13.000   1.4164   0.02203   0.01608   0.0094   0.1577   1.0000
  13.250   1.4256   0.02309   0.01717   0.0105   0.1555   1.0000
  13.500   1.4332   0.02436   0.01847   0.0115   0.1535   1.0000
  13.750   1.4406   0.02573   0.01988   0.0123   0.1516   1.0000
  14.000   1.4522   0.02687   0.02110   0.0128   0.1499   1.0000
  14.250   1.4621   0.02819   0.02249   0.0132   0.1480   1.0000
  14.500   1.4699   0.02973   0.02409   0.0135   0.1458   1.0000
  14.750   1.4753   0.03152   0.02593   0.0138   0.1435   1.0000
  15.000   1.4785   0.03357   0.02803   0.0139   0.1415   1.0000
  15.250   1.4796   0.03586   0.03035   0.0139   0.1395   1.0000
  15.500   1.4862   0.03768   0.03226   0.0139   0.1377   1.0000
  15.750   1.4906   0.03974   0.03440   0.0138   0.1358   1.0000
  16.000   1.4920   0.04213   0.03686   0.0136   0.1334   1.0000
  16.250   1.4897   0.04494   0.03972   0.0132   0.1310   1.0000
  16.500   1.4856   0.04798   0.04281   0.0127   0.1290   1.0000
  16.750   1.4827   0.05098   0.04588   0.0121   0.1267   1.0000
  17.000   1.4824   0.05379   0.04878   0.0115   0.1245   1.0000
  17.250   1.4783   0.05710   0.05216   0.0106   0.1217   1.0000
  17.500   1.4723   0.06068   0.05580   0.0096   0.1197   1.0000
  17.750   1.4599   0.06516   0.06032   0.0082   0.1167   1.0000
  18.000   1.4578   0.06838   0.06363   0.0072   0.1144   1.0000
  18.250   1.4515   0.07220   0.06753   0.0060   0.1120   1.0000
  18.500   1.4413   0.07663   0.07202   0.0044   0.1093   1.0000
  18.750   1.4258   0.08181   0.07724   0.0024   0.1065   1.0000
  19.000   1.4184   0.08599   0.08151   0.0009   0.1034   1.0000
  19.250   1.4085   0.09058   0.08616  -0.0009   0.1007   1.0000
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