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EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1213 AIRFOIL (e1213-il)
Reynolds number: 100,000
Max Cl/Cd: 39.37 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1213-il-100000-n5.txt
Download as CSV file: xf-e1213-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7507   0.09917   0.09302  -0.0179   1.0000   0.0703
 -14.750  -0.7520   0.09542   0.08931  -0.0197   1.0000   0.0741
 -14.500  -0.7667   0.08940   0.08325  -0.0228   1.0000   0.0779
 -14.250  -0.7733   0.08510   0.07899  -0.0250   1.0000   0.0820
 -14.000  -0.7966   0.07819   0.07200  -0.0287   1.0000   0.0860
 -13.750  -0.8090   0.07326   0.06709  -0.0312   1.0000   0.0902
 -13.500  -0.8399   0.06550   0.05921  -0.0356   1.0000   0.0935
 -13.250  -0.8610   0.05947   0.05316  -0.0389   1.0000   0.0966
 -13.000  -0.8890   0.05245   0.04604  -0.0432   1.0000   0.0992
 -12.750  -0.9179   0.04558   0.03901  -0.0477   1.0000   0.1017
 -12.500  -0.9392   0.04053   0.03380  -0.0505   1.0000   0.1048
 -12.250  -0.9529   0.03735   0.03056  -0.0510   1.0000   0.1082
 -12.000  -0.9616   0.03508   0.02816  -0.0498   1.0000   0.1131
 -11.750  -0.9654   0.03360   0.02665  -0.0476   1.0000   0.1177
 -11.500  -0.9633   0.03230   0.02525  -0.0456   1.0000   0.1238
 -11.250  -0.9554   0.03133   0.02425  -0.0439   1.0000   0.1296
 -11.000  -0.9454   0.03031   0.02309  -0.0423   1.0000   0.1364
 -10.750  -0.9319   0.02970   0.02250  -0.0409   1.0000   0.1425
 -10.500  -0.9187   0.02891   0.02155  -0.0394   1.0000   0.1507
 -10.250  -0.9015   0.02873   0.02142  -0.0381   1.0000   0.1581
 -10.000  -0.8856   0.02830   0.02089  -0.0367   1.0000   0.1659
  -9.750  -0.8671   0.02817   0.02076  -0.0353   1.0000   0.1730
  -9.500  -0.8505   0.02768   0.02015  -0.0339   1.0000   0.1794
  -9.250  -0.8302   0.02756   0.02008  -0.0326   1.0000   0.1843
  -9.000  -0.8139   0.02695   0.01932  -0.0311   1.0000   0.1899
  -8.750  -0.7965   0.02646   0.01878  -0.0296   1.0000   0.1943
  -8.500  -0.7752   0.02624   0.01862  -0.0286   0.9973   0.1984
  -8.250  -0.7361   0.02563   0.01782  -0.0313   0.9657   0.2050
  -8.000  -0.6959   0.02510   0.01718  -0.0339   0.9311   0.2104
  -7.750  -0.6539   0.02478   0.01678  -0.0365   0.9001   0.2157
  -7.500  -0.6198   0.02424   0.01597  -0.0377   0.8687   0.2217
  -7.250  -0.5903   0.02383   0.01537  -0.0379   0.8403   0.2261
  -7.000  -0.5633   0.02361   0.01508  -0.0374   0.8145   0.2300
  -6.750  -0.5383   0.02332   0.01461  -0.0366   0.7914   0.2346
  -6.500  -0.5145   0.02294   0.01393  -0.0357   0.7707   0.2397
  -6.250  -0.4893   0.02261   0.01351  -0.0350   0.7517   0.2435
  -6.000  -0.4638   0.02237   0.01321  -0.0343   0.7338   0.2473
  -5.750  -0.4384   0.02211   0.01281  -0.0336   0.7174   0.2518
  -5.500  -0.4133   0.02180   0.01228  -0.0328   0.7021   0.2568
  -5.250  -0.3876   0.02149   0.01184  -0.0322   0.6869   0.2607
  -5.000  -0.3612   0.02124   0.01157  -0.0317   0.6722   0.2646
  -4.750  -0.3351   0.02102   0.01125  -0.0311   0.6587   0.2692
  -4.500  -0.3091   0.02078   0.01083  -0.0305   0.6459   0.2741
  -4.250  -0.2827   0.02051   0.01045  -0.0301   0.6325   0.2784
  -4.000  -0.2563   0.02030   0.01021  -0.0295   0.6205   0.2825
  -3.750  -0.2298   0.02011   0.00995  -0.0290   0.6083   0.2873
  -3.500  -0.2032   0.01993   0.00965  -0.0286   0.5966   0.2925
  -3.250  -0.1767   0.01974   0.00933  -0.0280   0.5860   0.2971
  -3.000  -0.1500   0.01955   0.00917  -0.0276   0.5741   0.3016
  -2.750  -0.1234   0.01942   0.00894  -0.0271   0.5643   0.3070
  -2.500  -0.0964   0.01928   0.00872  -0.0267   0.5530   0.3127
  -2.250  -0.0697   0.01912   0.00852  -0.0262   0.5435   0.3176
  -2.000  -0.0430   0.01899   0.00841  -0.0258   0.5329   0.3231
  -1.750  -0.0162   0.01891   0.00823  -0.0253   0.5240   0.3297
  -1.500   0.0107   0.01880   0.00810  -0.0249   0.5137   0.3359
  -1.250   0.0372   0.01870   0.00798  -0.0244   0.5052   0.3419
  -1.000   0.0641   0.01863   0.00791  -0.0240   0.4953   0.3494
  -0.500   0.1173   0.01850   0.00779  -0.0231   0.4778   0.3653
  -0.250   0.1441   0.01847   0.00769  -0.0226   0.4699   0.3745
   0.000   0.1704   0.01841   0.00772  -0.0221   0.4612   0.3837
   0.250   0.1970   0.01839   0.00768  -0.0217   0.4530   0.3951
   0.500   0.2233   0.01837   0.00770  -0.0212   0.4452   0.4078
   0.750   0.2496   0.01835   0.00775  -0.0207   0.4369   0.4221
   1.000   0.2759   0.01834   0.00772  -0.0201   0.4302   0.4386
   1.250   0.3020   0.01834   0.00786  -0.0197   0.4216   0.4579
   1.500   0.3280   0.01833   0.00790  -0.0191   0.4145   0.4815
   1.750   0.3540   0.01834   0.00802  -0.0186   0.4073   0.5104
   2.000   0.3799   0.01833   0.00816  -0.0180   0.3996   0.5447
   2.250   0.4052   0.01831   0.00823  -0.0172   0.3936   0.5860
   2.500   0.4298   0.01831   0.00848  -0.0163   0.3859   0.6358
   2.750   0.4542   0.01827   0.00864  -0.0153   0.3792   0.6961
   3.000   0.4808   0.01825   0.00883  -0.0144   0.3731   0.7688
   3.250   0.5194   0.01834   0.00916  -0.0159   0.3647   0.8526
   3.500   0.5719   0.01853   0.00930  -0.0202   0.3574   0.9243
   3.750   0.6164   0.01882   0.00963  -0.0235   0.3490   0.9730
   4.000   0.6591   0.01909   0.00981  -0.0265   0.3420   1.0000
   4.250   0.6806   0.01939   0.01002  -0.0254   0.3370   1.0000
   4.500   0.7020   0.01971   0.01034  -0.0243   0.3308   1.0000
   4.750   0.7237   0.02000   0.01055  -0.0232   0.3254   1.0000
   5.000   0.7457   0.02032   0.01076  -0.0221   0.3208   1.0000
   5.250   0.7670   0.02071   0.01119  -0.0211   0.3149   1.0000
   5.500   0.7888   0.02107   0.01152  -0.0200   0.3098   1.0000
   5.750   0.8111   0.02141   0.01177  -0.0190   0.3055   1.0000
   6.000   0.8326   0.02184   0.01221  -0.0180   0.3006   1.0000
   6.250   0.8539   0.02227   0.01266  -0.0170   0.2953   1.0000
   6.500   0.8758   0.02265   0.01301  -0.0160   0.2907   1.0000
   6.750   0.8984   0.02305   0.01329  -0.0152   0.2869   1.0000
   7.000   0.9186   0.02360   0.01396  -0.0141   0.2822   1.0000
   7.250   0.9395   0.02411   0.01450  -0.0131   0.2778   1.0000
   7.500   0.9611   0.02455   0.01492  -0.0122   0.2738   1.0000
   7.750   0.9838   0.02499   0.01525  -0.0114   0.2704   1.0000
   8.000   1.0019   0.02566   0.01606  -0.0102   0.2659   1.0000
   8.250   1.0211   0.02625   0.01671  -0.0091   0.2617   1.0000
   8.500   1.0414   0.02679   0.01725  -0.0081   0.2582   1.0000
   8.750   1.0629   0.02731   0.01772  -0.0073   0.2553   1.0000
   9.000   1.0814   0.02801   0.01848  -0.0062   0.2520   1.0000
   9.250   1.0967   0.02883   0.01942  -0.0048   0.2482   1.0000
   9.500   1.1134   0.02953   0.02020  -0.0036   0.2446   1.0000
   9.750   1.1317   0.03015   0.02081  -0.0025   0.2415   1.0000
  10.000   1.1521   0.03072   0.02133  -0.0016   0.2389   1.0000
  10.250   1.1659   0.03165   0.02235  -0.0002   0.2362   1.0000
  10.500   1.1744   0.03276   0.02363   0.0016   0.2332   1.0000
  10.750   1.1831   0.03378   0.02475   0.0035   0.2302   1.0000
  11.000   1.1929   0.03466   0.02569   0.0053   0.2275   1.0000
  11.250   1.2068   0.03540   0.02642   0.0066   0.2250   1.0000
  11.500   1.2265   0.03602   0.02699   0.0074   0.2228   1.0000
  11.750   1.2220   0.03772   0.02887   0.0098   0.2204   1.0000
  12.000   1.2126   0.03991   0.03126   0.0117   0.2179   1.0000
  12.250   1.2047   0.04226   0.03377   0.0128   0.2153   1.0000
  12.500   1.2026   0.04441   0.03602   0.0135   0.2127   1.0000
  12.750   1.2104   0.04590   0.03754   0.0140   0.2104   1.0000
  13.000   1.2303   0.04650   0.03811   0.0145   0.2084   1.0000
  13.250   1.2230   0.04939   0.04111   0.0146   0.2062   1.0000
  13.500   0.9283   0.09053   0.08302  -0.0040   0.1914   1.0000
  13.750   0.9723   0.08675   0.07921  -0.0014   0.1921   1.0000
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