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EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1213 AIRFOIL (e1213-il)
Reynolds number: 500,000
Max Cl/Cd: 79.39 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1213-il-500000.txt
Download as CSV file: xf-e1213-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.9453   0.08688   0.08239  -0.0252   1.0000   0.0284
 -16.250  -0.9515   0.08259   0.07807  -0.0272   1.0000   0.0288
 -16.000  -0.9590   0.07818   0.07361  -0.0293   1.0000   0.0290
 -15.750  -0.9693   0.07355   0.06892  -0.0316   1.0000   0.0291
 -15.500  -0.9854   0.06832   0.06362  -0.0341   1.0000   0.0295
 -15.250  -1.0028   0.06299   0.05821  -0.0367   1.0000   0.0296
 -15.000  -1.0244   0.05713   0.05225  -0.0396   1.0000   0.0297
 -14.750  -1.0471   0.05106   0.04606  -0.0427   1.0000   0.0298
 -14.500  -1.0689   0.04494   0.03982  -0.0459   1.0000   0.0298
 -14.250  -1.0886   0.03884   0.03357  -0.0496   1.0000   0.0299
 -14.000  -1.1009   0.03386   0.02843  -0.0528   1.0000   0.0304
 -13.750  -1.1114   0.02997   0.02441  -0.0546   1.0000   0.0306
 -13.500  -1.1147   0.02762   0.02194  -0.0545   1.0000   0.0311
 -13.250  -1.1237   0.02549   0.01972  -0.0528   1.0000   0.0316
 -13.000  -1.1263   0.02410   0.01827  -0.0501   1.0000   0.0323
 -12.750  -1.1265   0.02301   0.01713  -0.0469   1.0000   0.0332
 -12.500  -1.1195   0.02209   0.01615  -0.0444   1.0000   0.0345
 -12.250  -1.1101   0.02111   0.01513  -0.0422   1.0000   0.0362
 -12.000  -1.0986   0.02017   0.01417  -0.0402   1.0000   0.0387
 -11.750  -1.0864   0.01921   0.01321  -0.0382   1.0000   0.0429
 -11.500  -1.0750   0.01813   0.01217  -0.0361   1.0000   0.0518
 -11.250  -1.0628   0.01705   0.01119  -0.0341   1.0000   0.0658
 -11.000  -1.0480   0.01616   0.01039  -0.0323   1.0000   0.0813
 -10.750  -1.0299   0.01552   0.00982  -0.0308   1.0000   0.0939
 -10.500  -1.0107   0.01499   0.00932  -0.0293   1.0000   0.1046
 -10.250  -0.9906   0.01454   0.00892  -0.0280   1.0000   0.1138
 -10.000  -0.9703   0.01413   0.00855  -0.0266   1.0000   0.1223
  -9.750  -0.9494   0.01378   0.00823  -0.0253   1.0000   0.1296
  -9.500  -0.9161   0.01349   0.00793  -0.0263   0.9950   0.1378
  -9.250  -0.8735   0.01311   0.00760  -0.0294   0.9789   0.1466
  -9.000  -0.8267   0.01279   0.00726  -0.0330   0.9431   0.1542
  -8.750  -0.7809   0.01259   0.00696  -0.0363   0.8938   0.1618
  -8.500  -0.7557   0.01251   0.00674  -0.0353   0.8481   0.1675
  -8.250  -0.7311   0.01248   0.00658  -0.0344   0.8155   0.1733
  -8.000  -0.7053   0.01247   0.00640  -0.0336   0.7887   0.1784
  -7.750  -0.6803   0.01236   0.00624  -0.0328   0.7656   0.1838
  -7.500  -0.6539   0.01234   0.00610  -0.0322   0.7449   0.1887
  -7.250  -0.6270   0.01232   0.00595  -0.0316   0.7255   0.1929
  -7.000  -0.6011   0.01217   0.00577  -0.0310   0.7079   0.1979
  -6.750  -0.5739   0.01215   0.00568  -0.0306   0.6911   0.2027
  -6.500  -0.5462   0.01218   0.00559  -0.0302   0.6754   0.2070
  -6.250  -0.5198   0.01202   0.00539  -0.0296   0.6609   0.2118
  -6.000  -0.4926   0.01198   0.00530  -0.0292   0.6465   0.2162
  -5.750  -0.4649   0.01195   0.00520  -0.0289   0.6326   0.2202
  -5.500  -0.4370   0.01195   0.00508  -0.0285   0.6199   0.2233
  -5.250  -0.4102   0.01175   0.00484  -0.0280   0.6072   0.2273
  -5.000  -0.3827   0.01163   0.00471  -0.0277   0.5949   0.2311
  -4.750  -0.3551   0.01159   0.00459  -0.0273   0.5834   0.2345
  -4.500  -0.3270   0.01154   0.00448  -0.0270   0.5718   0.2380
  -4.250  -0.2989   0.01154   0.00438  -0.0267   0.5608   0.2408
  -4.000  -0.2718   0.01133   0.00416  -0.0263   0.5498   0.2450
  -3.750  -0.2441   0.01124   0.00406  -0.0260   0.5398   0.2488
  -3.500  -0.2162   0.01120   0.00396  -0.0257   0.5292   0.2525
  -3.250  -0.1879   0.01117   0.00388  -0.0255   0.5193   0.2560
  -3.000  -0.1597   0.01118   0.00379  -0.0252   0.5094   0.2586
  -2.750  -0.1323   0.01099   0.00363  -0.0248   0.5004   0.2635
  -2.500  -0.1046   0.01094   0.00355  -0.0245   0.4907   0.2676
  -2.250  -0.0764   0.01090   0.00349  -0.0243   0.4817   0.2714
  -2.000  -0.0482   0.01090   0.00342  -0.0240   0.4727   0.2751
  -1.750  -0.0203   0.01085   0.00334  -0.0238   0.4644   0.2793
  -1.500   0.0074   0.01076   0.00326  -0.0234   0.4555   0.2843
  -1.250   0.0352   0.01075   0.00322  -0.0232   0.4472   0.2889
  -1.000   0.0636   0.01073   0.00318  -0.0230   0.4389   0.2934
  -0.500   0.1192   0.01065   0.00310  -0.0224   0.4229   0.3046
  -0.250   0.1470   0.01067   0.00308  -0.0221   0.4150   0.3104
   0.000   0.1751   0.01067   0.00306  -0.0219   0.4076   0.3164
   0.250   0.2027   0.01062   0.00305  -0.0216   0.3998   0.3244
   0.500   0.2304   0.01067   0.00306  -0.0213   0.3923   0.3325
   0.750   0.2583   0.01061   0.00306  -0.0210   0.3852   0.3418
   1.000   0.2858   0.01065   0.00307  -0.0207   0.3778   0.3523
   1.250   0.3134   0.01062   0.00311  -0.0205   0.3712   0.3653
   1.500   0.3409   0.01060   0.00314  -0.0202   0.3645   0.3811
   1.750   0.3678   0.01064   0.00319  -0.0198   0.3577   0.4003
   2.000   0.3953   0.01059   0.00324  -0.0195   0.3515   0.4240
   2.250   0.4223   0.01057   0.00330  -0.0192   0.3448   0.4525
   2.500   0.4485   0.01058   0.00339  -0.0187   0.3386   0.4866
   2.750   0.4753   0.01050   0.00347  -0.0183   0.3332   0.5281
   3.000   0.5012   0.01044   0.00357  -0.0177   0.3273   0.5782
   3.250   0.5258   0.01043   0.00370  -0.0169   0.3213   0.6358
   3.500   0.5508   0.01028   0.00381  -0.0161   0.3161   0.7003
   3.750   0.5741   0.01016   0.00394  -0.0149   0.3104   0.7742
   4.000   0.5971   0.01012   0.00412  -0.0134   0.3047   0.8609
   4.250   0.6511   0.01019   0.00436  -0.0183   0.2984   0.9430
   4.500   0.6992   0.01040   0.00453  -0.0222   0.2918   0.9733
   4.750   0.7403   0.01066   0.00472  -0.0248   0.2857   0.9886
   5.000   0.7851   0.01079   0.00485  -0.0281   0.2796   0.9972
   5.250   0.8182   0.01100   0.00499  -0.0292   0.2740   1.0000
   5.500   0.8404   0.01124   0.00518  -0.0280   0.2694   1.0000
   5.750   0.8641   0.01137   0.00533  -0.0271   0.2653   1.0000
   6.000   0.8872   0.01156   0.00549  -0.0261   0.2608   1.0000
   6.250   0.9094   0.01182   0.00570  -0.0250   0.2563   1.0000
   6.500   0.9323   0.01206   0.00592  -0.0239   0.2523   1.0000
   6.750   0.9560   0.01223   0.00611  -0.0231   0.2483   1.0000
   7.000   0.9790   0.01245   0.00631  -0.0221   0.2440   1.0000
   7.250   1.0007   0.01276   0.00656  -0.0209   0.2397   1.0000
   7.500   1.0233   0.01302   0.00683  -0.0199   0.2362   1.0000
   7.750   1.0467   0.01322   0.00706  -0.0190   0.2329   1.0000
   8.000   1.0694   0.01347   0.00731  -0.0180   0.2294   1.0000
   8.250   1.0910   0.01378   0.00759  -0.0169   0.2259   1.0000
   8.500   1.1115   0.01420   0.00796  -0.0157   0.2221   1.0000
   8.750   1.1348   0.01440   0.00822  -0.0148   0.2194   1.0000
   9.000   1.1574   0.01465   0.00850  -0.0139   0.2163   1.0000
   9.250   1.1791   0.01496   0.00881  -0.0128   0.2133   1.0000
   9.500   1.1995   0.01533   0.00916  -0.0116   0.2104   1.0000
   9.750   1.2183   0.01585   0.00964  -0.0103   0.2071   1.0000
  10.000   1.2403   0.01610   0.00996  -0.0093   0.2052   1.0000
  10.250   1.2613   0.01640   0.01031  -0.0082   0.2027   1.0000
  10.500   1.2814   0.01673   0.01066  -0.0071   0.2001   1.0000
  10.750   1.3001   0.01712   0.01106  -0.0057   0.1978   1.0000
  11.000   1.3169   0.01759   0.01152  -0.0042   0.1952   1.0000
  11.250   1.3311   0.01820   0.01210  -0.0023   0.1924   1.0000
  11.500   1.3464   0.01853   0.01252  -0.0004   0.1908   1.0000
  11.750   1.3608   0.01893   0.01298   0.0015   0.1888   1.0000
  12.000   1.3747   0.01939   0.01349   0.0034   0.1867   1.0000
  12.250   1.3879   0.01991   0.01405   0.0051   0.1846   1.0000
  12.500   1.3998   0.02055   0.01470   0.0068   0.1825   1.0000
  12.750   1.4102   0.02136   0.01550   0.0085   0.1801   1.0000
  13.000   1.4218   0.02220   0.01637   0.0099   0.1780   1.0000
  13.250   1.4339   0.02295   0.01721   0.0111   0.1763   1.0000
  13.500   1.4454   0.02382   0.01816   0.0121   0.1743   1.0000
  13.750   1.4562   0.02479   0.01918   0.0130   0.1722   1.0000
  14.000   1.4662   0.02587   0.02031   0.0138   0.1701   1.0000
  14.250   1.4750   0.02711   0.02156   0.0146   0.1681   1.0000
  14.500   1.4828   0.02847   0.02290   0.0154   0.1654   1.0000
  14.750   1.4912   0.02984   0.02438   0.0158   0.1637   1.0000
  15.000   1.4993   0.03131   0.02595   0.0161   0.1620   1.0000
  15.250   1.5064   0.03292   0.02764   0.0163   0.1598   1.0000
  15.500   1.5124   0.03464   0.02943   0.0164   0.1577   1.0000
  15.750   1.5172   0.03652   0.03133   0.0165   0.1556   1.0000
  16.000   1.5204   0.03849   0.03330   0.0166   0.1531   1.0000
  16.250   1.5239   0.04053   0.03541   0.0166   0.1511   1.0000
  16.500   1.5259   0.04286   0.03786   0.0162   0.1492   1.0000
  16.750   1.5262   0.04540   0.04050   0.0157   0.1467   1.0000
  17.000   1.5268   0.04795   0.04311   0.0152   0.1446   1.0000
  17.250   1.5253   0.05074   0.04593   0.0146   0.1423   1.0000
  17.500   1.5253   0.05327   0.04844   0.0143   0.1397   1.0000
  17.750   1.5216   0.05661   0.05193   0.0132   0.1378   1.0000
  18.000   1.5185   0.05989   0.05532   0.0122   0.1356   1.0000
  18.250   1.5143   0.06336   0.05887   0.0110   0.1331   1.0000
  18.500   1.5088   0.06697   0.06251   0.0098   0.1307   1.0000
  18.750   1.5045   0.07034   0.06586   0.0088   0.1279   1.0000
  19.000   1.4947   0.07483   0.07051   0.0069   0.1255   1.0000
  19.250   1.4864   0.07907   0.07485   0.0053   0.1228   1.0000
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