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EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1213 AIRFOIL (e1213-il)
Reynolds number: 200,000
Max Cl/Cd: 55.85 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1213-il-200000-n5.txt
Download as CSV file: xf-e1213-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.8384   0.09075   0.08527  -0.0214   1.0000   0.0386
 -15.250  -0.8474   0.08581   0.08027  -0.0239   1.0000   0.0396
 -15.000  -0.8638   0.07991   0.07432  -0.0270   1.0000   0.0406
 -14.750  -0.8834   0.07387   0.06821  -0.0302   1.0000   0.0414
 -14.500  -0.9043   0.06778   0.06204  -0.0334   1.0000   0.0419
 -14.250  -0.9287   0.06128   0.05543  -0.0368   1.0000   0.0425
 -14.000  -0.9549   0.05457   0.04860  -0.0404   1.0000   0.0432
 -13.750  -0.9800   0.04793   0.04181  -0.0443   1.0000   0.0440
 -13.500  -0.9998   0.04199   0.03571  -0.0479   1.0000   0.0446
 -13.250  -1.0186   0.03662   0.03020  -0.0512   1.0000   0.0457
 -13.000  -1.0310   0.03294   0.02639  -0.0525   1.0000   0.0472
 -12.750  -1.0390   0.03045   0.02379  -0.0520   1.0000   0.0500
 -12.500  -1.0458   0.02852   0.02181  -0.0501   1.0000   0.0532
 -12.250  -1.0485   0.02710   0.02035  -0.0473   1.0000   0.0574
 -12.000  -1.0462   0.02586   0.01908  -0.0448   1.0000   0.0630
 -11.750  -1.0385   0.02473   0.01793  -0.0428   1.0000   0.0697
 -11.500  -1.0281   0.02369   0.01689  -0.0410   1.0000   0.0775
 -11.250  -1.0147   0.02280   0.01599  -0.0394   1.0000   0.0856
 -11.000  -0.9996   0.02200   0.01519  -0.0379   1.0000   0.0941
 -10.750  -0.9832   0.02128   0.01448  -0.0364   1.0000   0.1025
 -10.500  -0.9656   0.02064   0.01385  -0.0351   1.0000   0.1107
 -10.250  -0.9469   0.02009   0.01330  -0.0338   1.0000   0.1182
 -10.000  -0.9271   0.01961   0.01279  -0.0325   1.0000   0.1258
  -9.750  -0.9080   0.01915   0.01235  -0.0312   1.0000   0.1325
  -9.500  -0.8879   0.01876   0.01193  -0.0299   1.0000   0.1391
  -9.250  -0.8508   0.01832   0.01148  -0.0320   0.9728   0.1483
  -9.000  -0.8076   0.01797   0.01110  -0.0351   0.9249   0.1582
  -8.750  -0.7653   0.01769   0.01070  -0.0378   0.8833   0.1669
  -8.500  -0.7345   0.01755   0.01040  -0.0381   0.8450   0.1745
  -8.250  -0.7082   0.01742   0.01014  -0.0376   0.8144   0.1807
  -8.000  -0.6833   0.01734   0.00994  -0.0368   0.7885   0.1865
  -7.750  -0.6582   0.01723   0.00959  -0.0359   0.7658   0.1921
  -7.500  -0.6336   0.01707   0.00939  -0.0351   0.7456   0.1962
  -7.250  -0.6084   0.01695   0.00916  -0.0343   0.7268   0.2004
  -7.000  -0.5828   0.01680   0.00885  -0.0337   0.7092   0.2048
  -6.750  -0.5570   0.01663   0.00853  -0.0330   0.6929   0.2087
  -6.500  -0.5313   0.01646   0.00832  -0.0324   0.6776   0.2122
  -6.250  -0.5053   0.01634   0.00809  -0.0317   0.6630   0.2160
  -6.000  -0.4789   0.01620   0.00783  -0.0312   0.6487   0.2201
  -5.750  -0.4522   0.01608   0.00754  -0.0307   0.6352   0.2239
  -5.500  -0.4260   0.01588   0.00732  -0.0302   0.6226   0.2273
  -5.250  -0.3994   0.01574   0.00713  -0.0297   0.6098   0.2308
  -5.000  -0.3725   0.01562   0.00691  -0.0292   0.5978   0.2347
  -4.750  -0.3456   0.01553   0.00668  -0.0287   0.5862   0.2387
  -4.500  -0.3184   0.01538   0.00646  -0.0283   0.5745   0.2422
  -4.250  -0.2917   0.01523   0.00628  -0.0279   0.5640   0.2456
  -4.000  -0.2645   0.01511   0.00612  -0.0275   0.5528   0.2494
  -3.750  -0.2373   0.01503   0.00595  -0.0271   0.5428   0.2536
  -3.500  -0.2098   0.01495   0.00577  -0.0267   0.5321   0.2574
  -3.250  -0.1827   0.01482   0.00560  -0.0263   0.5226   0.2609
  -3.000  -0.1556   0.01471   0.00548  -0.0259   0.5126   0.2649
  -2.750  -0.1283   0.01464   0.00536  -0.0255   0.5034   0.2692
  -2.500  -0.1008   0.01457   0.00523  -0.0252   0.4938   0.2735
  -2.250  -0.0733   0.01453   0.00510  -0.0248   0.4853   0.2776
  -2.000  -0.0462   0.01441   0.00502  -0.0245   0.4758   0.2820
  -1.750  -0.0191   0.01437   0.00493  -0.0241   0.4677   0.2868
  -1.500   0.0086   0.01431   0.00485  -0.0238   0.4589   0.2917
  -1.250   0.0359   0.01430   0.00476  -0.0234   0.4508   0.2964
  -1.000   0.0631   0.01421   0.00472  -0.0231   0.4425   0.3017
  -0.750   0.0903   0.01419   0.00468  -0.0227   0.4344   0.3078
  -0.500   0.1178   0.01419   0.00463  -0.0224   0.4270   0.3139
  -0.250   0.1450   0.01414   0.00461  -0.0220   0.4188   0.3197
   0.000   0.1718   0.01415   0.00459  -0.0216   0.4117   0.3269
   0.250   0.1994   0.01414   0.00460  -0.0213   0.4040   0.3350
   0.500   0.2262   0.01412   0.00460  -0.0209   0.3967   0.3438
   0.750   0.2534   0.01415   0.00462  -0.0205   0.3897   0.3536
   1.000   0.2802   0.01413   0.00466  -0.0202   0.3822   0.3639
   1.250   0.3068   0.01417   0.00468  -0.0197   0.3757   0.3760
   1.500   0.3338   0.01417   0.00475  -0.0194   0.3687   0.3910
   1.750   0.3603   0.01417   0.00481  -0.0189   0.3617   0.4082
   2.000   0.3864   0.01421   0.00488  -0.0185   0.3557   0.4279
   2.250   0.4130   0.01420   0.00499  -0.0180   0.3490   0.4505
   2.500   0.4388   0.01423   0.00508  -0.0175   0.3425   0.4764
   2.750   0.4644   0.01424   0.00520  -0.0169   0.3369   0.5086
   3.000   0.4899   0.01421   0.00534  -0.0163   0.3309   0.5473
   3.250   0.5145   0.01420   0.00548  -0.0155   0.3252   0.5929
   3.500   0.5386   0.01419   0.00563  -0.0145   0.3199   0.6449
   3.750   0.5628   0.01414   0.00582  -0.0135   0.3139   0.7040
   4.000   0.5872   0.01410   0.00601  -0.0125   0.3084   0.7761
   4.250   0.6230   0.01416   0.00626  -0.0135   0.3030   0.8660
   4.500   0.6801   0.01436   0.00655  -0.0191   0.2958   0.9397
   4.750   0.7201   0.01461   0.00676  -0.0215   0.2898   0.9775
   5.000   0.7611   0.01488   0.00699  -0.0242   0.2840   0.9970
   5.250   0.7879   0.01511   0.00720  -0.0240   0.2787   1.0000
   5.500   0.8101   0.01536   0.00741  -0.0229   0.2742   1.0000
   5.750   0.8317   0.01567   0.00763  -0.0218   0.2703   1.0000
   6.000   0.8547   0.01590   0.00790  -0.0208   0.2661   1.0000
   6.250   0.8771   0.01617   0.00817  -0.0198   0.2616   1.0000
   6.500   0.8991   0.01647   0.00843  -0.0187   0.2574   1.0000
   6.750   0.9205   0.01681   0.00870  -0.0176   0.2536   1.0000
   7.000   0.9433   0.01709   0.00903  -0.0167   0.2494   1.0000
   7.250   0.9654   0.01740   0.00935  -0.0157   0.2455   1.0000
   7.500   0.9871   0.01774   0.00967  -0.0147   0.2419   1.0000
   7.750   1.0081   0.01813   0.01001  -0.0136   0.2387   1.0000
   8.000   1.0299   0.01848   0.01040  -0.0126   0.2354   1.0000
   8.250   1.0516   0.01883   0.01080  -0.0116   0.2317   1.0000
   8.500   1.0724   0.01921   0.01119  -0.0106   0.2281   1.0000
   8.750   1.0925   0.01963   0.01158  -0.0094   0.2249   1.0000
   9.000   1.1120   0.02010   0.01201  -0.0083   0.2222   1.0000
   9.250   1.1325   0.02051   0.01251  -0.0072   0.2193   1.0000
   9.500   1.1521   0.02095   0.01300  -0.0061   0.2164   1.0000
   9.750   1.1708   0.02141   0.01350  -0.0048   0.2135   1.0000
  10.000   1.1884   0.02190   0.01399  -0.0035   0.2108   1.0000
  10.250   1.2049   0.02244   0.01451  -0.0020   0.2083   1.0000
  10.500   1.2211   0.02298   0.01509  -0.0006   0.2059   1.0000
  10.750   1.2353   0.02352   0.01571   0.0012   0.2035   1.0000
  11.000   1.2482   0.02411   0.01637   0.0031   0.2012   1.0000
  11.250   1.2604   0.02474   0.01706   0.0049   0.1988   1.0000
  11.500   1.2721   0.02543   0.01777   0.0066   0.1966   1.0000
  11.750   1.2837   0.02618   0.01852   0.0081   0.1944   1.0000
  12.000   1.2960   0.02701   0.01933   0.0095   0.1924   1.0000
  12.250   1.3059   0.02794   0.02040   0.0108   0.1904   1.0000
  12.500   1.3155   0.02896   0.02152   0.0119   0.1882   1.0000
  12.750   1.3243   0.03007   0.02272   0.0130   0.1859   1.0000
  13.000   1.3326   0.03127   0.02398   0.0139   0.1837   1.0000
  13.250   1.3411   0.03251   0.02526   0.0146   0.1817   1.0000
  13.500   1.3503   0.03375   0.02649   0.0153   0.1796   1.0000
  13.750   1.3584   0.03516   0.02794   0.0159   0.1776   1.0000
  14.000   1.3620   0.03696   0.02990   0.0162   0.1755   1.0000
  14.250   1.3659   0.03882   0.03188   0.0165   0.1734   1.0000
  14.500   1.3686   0.04083   0.03399   0.0166   0.1711   1.0000
  14.750   1.3717   0.04284   0.03607   0.0166   0.1691   1.0000
  15.000   1.3768   0.04471   0.03795   0.0166   0.1670   1.0000
  15.250   1.3858   0.04618   0.03938   0.0168   0.1649   1.0000
  15.500   1.3795   0.04934   0.04274   0.0161   0.1629   1.0000
  15.750   1.3734   0.05260   0.04616   0.0154   0.1605   1.0000
  16.000   1.3683   0.05582   0.04951   0.0145   0.1583   1.0000
  16.250   1.3643   0.05901   0.05278   0.0136   0.1559   1.0000
  16.500   1.3659   0.06159   0.05538   0.0129   0.1539   1.0000
  16.750   1.3734   0.06340   0.05716   0.0127   0.1518   1.0000
  17.000   1.3528   0.06910   0.06310   0.0103   0.1495   1.0000
  17.250   1.3327   0.07495   0.06913   0.0078   0.1468   1.0000
  17.500   1.3176   0.08025   0.07456   0.0054   0.1442   1.0000
  17.750   1.3144   0.08391   0.07825   0.0039   0.1418   1.0000
  18.000   1.3278   0.08502   0.07932   0.0038   0.1397   1.0000
  18.250   1.2639   0.09829   0.09293  -0.0029   0.1360   1.0000
  18.500   1.2036   0.11168   0.10654  -0.0098   0.1314   1.0000
  18.750   1.2177   0.11278   0.10763  -0.0102   0.1295   1.0000
  19.000   1.2490   0.11095   0.10573  -0.0089   0.1280   1.0000
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