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EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1213 AIRFOIL (e1213-il)
Reynolds number: 50,000
Max Cl/Cd: 22.29 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1213-il-50000-n5.txt
Download as CSV file: xf-e1213-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5178   0.11822   0.11014  -0.0090   1.0000   0.1391
 -12.500  -0.5028   0.11690   0.10880  -0.0088   1.0000   0.1443
 -12.250  -0.5242   0.10971   0.10163  -0.0130   1.0000   0.1506
 -12.000  -0.5004   0.10973   0.10163  -0.0116   1.0000   0.1549
 -11.750  -0.5057   0.10520   0.09710  -0.0137   1.0000   0.1605
 -11.500  -0.5092   0.10100   0.09291  -0.0156   1.0000   0.1657
 -11.250  -0.4963   0.09926   0.09115  -0.0155   1.0000   0.1702
 -11.000  -0.5340   0.09026   0.08220  -0.0211   1.0000   0.1777
 -10.750  -0.5058   0.09081   0.08272  -0.0191   1.0000   0.1809
 -10.500  -0.4995   0.08827   0.08018  -0.0197   1.0000   0.1860
 -10.250  -0.5400   0.07923   0.07121  -0.0252   1.0000   0.1932
 -10.000  -0.5142   0.07952   0.07149  -0.0235   1.0000   0.1966
  -9.500  -0.5883   0.06325   0.05531  -0.0331   1.0000   0.2103
  -9.250  -0.5687   0.06291   0.05498  -0.0318   1.0000   0.2143
  -9.000  -0.6508   0.05304   0.04500  -0.0338   1.0000   0.2212
  -8.750  -0.6662   0.04933   0.04116  -0.0329   1.0000   0.2261
  -8.500  -0.6444   0.04904   0.04093  -0.0317   1.0000   0.2301
  -8.250  -0.6460   0.04667   0.03847  -0.0304   1.0000   0.2355
  -8.000  -0.6648   0.04290   0.03438  -0.0285   1.0000   0.2415
  -7.750  -0.6452   0.04271   0.03433  -0.0269   1.0000   0.2449
  -7.500  -0.6376   0.04193   0.03360  -0.0248   1.0000   0.2489
  -7.250  -0.6188   0.03980   0.03120  -0.0266   0.9782   0.2558
  -7.000  -0.5796   0.03839   0.02962  -0.0302   0.9499   0.2622
  -6.750  -0.5381   0.03745   0.02858  -0.0333   0.9243   0.2683
  -6.500  -0.5063   0.03541   0.02604  -0.0363   0.8999   0.2768
  -6.250  -0.4672   0.03486   0.02551  -0.0380   0.8765   0.2816
  -6.000  -0.4359   0.03409   0.02458  -0.0388   0.8531   0.2873
  -5.750  -0.4124   0.03296   0.02307  -0.0388   0.8309   0.2942
  -5.500  -0.3861   0.03236   0.02236  -0.0384   0.8103   0.2990
  -5.250  -0.3608   0.03189   0.02177  -0.0377   0.7908   0.3039
  -5.000  -0.3383   0.03125   0.02089  -0.0369   0.7725   0.3100
  -4.750  -0.3162   0.03056   0.01994  -0.0361   0.7554   0.3160
  -4.500  -0.2911   0.03022   0.01956  -0.0352   0.7392   0.3207
  -4.250  -0.2669   0.02977   0.01895  -0.0344   0.7245   0.3264
  -4.000  -0.2443   0.02923   0.01815  -0.0336   0.7088   0.3332
  -3.750  -0.2194   0.02890   0.01780  -0.0328   0.6940   0.3383
  -3.500  -0.1944   0.02858   0.01738  -0.0321   0.6807   0.3441
  -3.250  -0.1700   0.02819   0.01680  -0.0314   0.6675   0.3509
  -3.000  -0.1450   0.02789   0.01644  -0.0308   0.6539   0.3569
  -2.750  -0.1193   0.02764   0.01612  -0.0300   0.6422   0.3634
  -2.500  -0.0942   0.02737   0.01570  -0.0295   0.6295   0.3709
  -2.250  -0.0685   0.02715   0.01545  -0.0289   0.6175   0.3775
  -2.000  -0.0421   0.02694   0.01518  -0.0283   0.6067   0.3851
  -1.750  -0.0162   0.02679   0.01492  -0.0280   0.5944   0.3939
  -1.500   0.0111   0.02659   0.01470  -0.0274   0.5849   0.4017
  -1.250   0.0371   0.02652   0.01459  -0.0271   0.5728   0.4113
  -1.000   0.0644   0.02638   0.01443  -0.0267   0.5633   0.4206
  -0.750   0.0906   0.02634   0.01435  -0.0263   0.5520   0.4322
  -0.500   0.1171   0.02625   0.01428  -0.0258   0.5430   0.4431
  -0.250   0.1428   0.02624   0.01429  -0.0253   0.5324   0.4562
   0.000   0.1689   0.02617   0.01420  -0.0247   0.5237   0.4711
   0.250   0.1938   0.02620   0.01435  -0.0241   0.5135   0.4870
   0.500   0.2198   0.02612   0.01426  -0.0233   0.5059   0.5062
   0.750   0.2435   0.02622   0.01454  -0.0226   0.4954   0.5276
   1.000   0.2691   0.02612   0.01446  -0.0217   0.4882   0.5547
   1.250   0.2913   0.02627   0.01488  -0.0207   0.4784   0.5849
   1.500   0.3155   0.02620   0.01494  -0.0195   0.4710   0.6242
   1.750   0.3380   0.02630   0.01530  -0.0182   0.4623   0.6724
   2.000   0.3633   0.02632   0.01558  -0.0170   0.4542   0.7342
   2.250   0.3994   0.02641   0.01586  -0.0175   0.4462   0.8119
   2.500   0.4510   0.02672   0.01627  -0.0214   0.4355   0.8941
   2.750   0.5054   0.02708   0.01655  -0.0263   0.4262   0.9620
   3.000   0.5480   0.02751   0.01690  -0.0295   0.4170   1.0000
   3.250   0.5689   0.02773   0.01687  -0.0283   0.4116   1.0000
   3.500   0.5834   0.02854   0.01773  -0.0269   0.4031   1.0000
   3.750   0.6037   0.02893   0.01799  -0.0257   0.3970   1.0000
   4.000   0.6239   0.02940   0.01834  -0.0245   0.3912   1.0000
   4.250   0.6394   0.03025   0.01923  -0.0232   0.3835   1.0000
   4.500   0.6614   0.03062   0.01947  -0.0221   0.3779   1.0000
   4.750   0.6802   0.03131   0.02013  -0.0209   0.3720   1.0000
   5.000   0.6953   0.03228   0.02115  -0.0196   0.3649   1.0000
   5.250   0.7178   0.03269   0.02146  -0.0186   0.3598   1.0000
   5.500   0.7365   0.03346   0.02219  -0.0175   0.3544   1.0000
   5.750   0.7481   0.03476   0.02359  -0.0161   0.3476   1.0000
   6.000   0.7694   0.03532   0.02410  -0.0151   0.3427   1.0000
   6.250   0.7946   0.03565   0.02429  -0.0144   0.3387   1.0000
   6.500   0.7948   0.03779   0.02667  -0.0125   0.3315   1.0000
   6.750   0.8112   0.03873   0.02761  -0.0114   0.3265   1.0000
   7.000   0.8372   0.03902   0.02780  -0.0107   0.3229   1.0000
   7.250   0.8353   0.04136   0.03031  -0.0088   0.3172   1.0000
   7.500   0.8316   0.04374   0.03281  -0.0070   0.3114   1.0000
   7.750   0.8503   0.04450   0.03353  -0.0061   0.3075   1.0000
   8.000   0.8835   0.04433   0.03325  -0.0057   0.3046   1.0000
   8.250   0.7624   0.05581   0.04513  -0.0027   0.2942   1.0000
   8.500   0.7692   0.05786   0.04717  -0.0023   0.2903   1.0000
   8.750   0.8005   0.05739   0.04666  -0.0011   0.2882   1.0000
   9.250   0.7117   0.07497   0.06438  -0.0070   0.2715   1.0000
   9.750   0.6555   0.09008   0.07956  -0.0128   0.2584   1.0000
  10.000   0.6724   0.09136   0.08084  -0.0124   0.2558   1.0000
  10.250   0.6959   0.09176   0.08121  -0.0114   0.2540   1.0000
  10.750   0.6479   0.10611   0.09566  -0.0175   0.2432   1.0000
  11.000   0.6610   0.10809   0.09765  -0.0175   0.2405   1.0000
  11.250   0.6817   0.10904   0.09862  -0.0168   0.2385   1.0000
  11.500   0.6556   0.11654   0.10616  -0.0204   0.2334   1.0000
  11.750   0.6526   0.12092   0.11058  -0.0220   0.2303   1.0000
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