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EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1200 AIRFOIL (e1200-il)
Reynolds number: 100,000
Max Cl/Cd: 39.54 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1200-il-100000-n5.txt
Download as CSV file: xf-e1200-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1200 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3140   0.09878   0.09362  -0.0835   0.9625   0.0351
 -12.000  -0.3354   0.08611   0.08091  -0.0922   0.9570   0.0346
 -11.750  -0.3836   0.07012   0.06471  -0.1059   0.9480   0.0337
 -11.500  -0.4143   0.06059   0.05483  -0.1152   0.9400   0.0331
 -11.250  -0.4317   0.05496   0.04887  -0.1198   0.9297   0.0333
 -11.000  -0.4422   0.05048   0.04404  -0.1228   0.9205   0.0334
 -10.750  -0.4481   0.04711   0.04033  -0.1241   0.9113   0.0338
 -10.500  -0.4549   0.04456   0.03745  -0.1232   0.9012   0.0342
 -10.250  -0.4564   0.04213   0.03465  -0.1222   0.8939   0.0347
 -10.000  -0.4548   0.04011   0.03229  -0.1206   0.8865   0.0350
  -9.750  -0.4458   0.03813   0.02997  -0.1195   0.8806   0.0353
  -9.500  -0.4300   0.03613   0.02759  -0.1192   0.8766   0.0358
  -9.250  -0.4166   0.03475   0.02608  -0.1179   0.8707   0.0363
  -9.000  -0.3988   0.03351   0.02475  -0.1172   0.8657   0.0369
  -8.750  -0.3773   0.03228   0.02340  -0.1170   0.8620   0.0377
  -8.500  -0.3541   0.03118   0.02215  -0.1170   0.8592   0.0391
  -8.250  -0.3404   0.03046   0.02132  -0.1152   0.8538   0.0404
  -8.000  -0.3211   0.02960   0.02027  -0.1142   0.8496   0.0421
  -7.750  -0.2992   0.02863   0.01928  -0.1137   0.8462   0.0434
  -7.500  -0.2760   0.02774   0.01837  -0.1135   0.8434   0.0450
  -7.250  -0.2607   0.02718   0.01776  -0.1118   0.8389   0.0465
  -7.000  -0.2455   0.02665   0.01717  -0.1101   0.8345   0.0483
  -6.750  -0.2273   0.02605   0.01650  -0.1089   0.8310   0.0509
  -6.500  -0.2072   0.02542   0.01588  -0.1082   0.8281   0.0546
  -6.250  -0.1844   0.02480   0.01516  -0.1077   0.8257   0.0596
  -6.000  -0.1773   0.02454   0.01496  -0.1047   0.8200   0.0639
  -5.750  -0.1618   0.02410   0.01453  -0.1031   0.8161   0.0716
  -5.500  -0.1428   0.02356   0.01406  -0.1021   0.8132   0.0859
  -5.250  -0.1208   0.02296   0.01358  -0.1016   0.8107   0.1123
  -5.000  -0.1006   0.02248   0.01324  -0.1008   0.8079   0.1465
  -4.750  -0.0927   0.02237   0.01330  -0.0980   0.8023   0.1796
  -4.500  -0.0769   0.02187   0.01312  -0.0967   0.7988   0.2406
  -4.250  -0.0600   0.02097   0.01282  -0.0959   0.7959   0.3535
  -4.000  -0.0408   0.02053   0.01318  -0.0941   0.7937   0.4979
  -3.750  -0.0208   0.02092   0.01369  -0.0921   0.7905   0.5643
  -3.500  -0.0098   0.02149   0.01424  -0.0892   0.7852   0.5982
  -3.250   0.0120   0.02189   0.01456  -0.0878   0.7818   0.6252
  -3.000   0.0388   0.02215   0.01468  -0.0874   0.7793   0.6487
  -2.750   0.0673   0.02238   0.01478  -0.0871   0.7773   0.6667
  -2.500   0.0956   0.02266   0.01498  -0.0866   0.7757   0.6801
  -2.250   0.0949   0.02346   0.01580  -0.0819   0.7681   0.6898
  -2.000   0.1172   0.02375   0.01600  -0.0808   0.7647   0.7030
  -1.750   0.1427   0.02401   0.01618  -0.0799   0.7623   0.7164
  -1.500   0.1686   0.02425   0.01638  -0.0786   0.7604   0.7277
  -1.250   0.1730   0.02489   0.01701  -0.0749   0.7538   0.7381
  -1.000   0.1894   0.02522   0.01731  -0.0729   0.7492   0.7472
  -0.750   0.2164   0.02526   0.01727  -0.0727   0.7465   0.7543
  -0.500   0.2465   0.02522   0.01715  -0.0728   0.7444   0.7597
  -0.250   0.2618   0.02556   0.01744  -0.0714   0.7391   0.7665
   0.000   0.2735   0.02593   0.01781  -0.0690   0.7328   0.7711
   0.250   0.3023   0.02588   0.01770  -0.0691   0.7300   0.7752
   0.500   0.3366   0.02571   0.01746  -0.0703   0.7280   0.7797
   0.750   0.3694   0.02562   0.01729  -0.0715   0.7253   0.7845
   1.250   0.3983   0.02613   0.01781  -0.0675   0.7127   0.7922
   1.500   0.4371   0.02581   0.01744  -0.0692   0.7108   0.7960
   2.000   0.4668   0.02627   0.01791  -0.0656   0.6969   0.8046
   2.250   0.5071   0.02580   0.01741  -0.0673   0.6948   0.8078
   2.750   0.5435   0.02597   0.01758  -0.0647   0.6803   0.8169
   3.000   0.5725   0.02564   0.01726  -0.0645   0.6754   0.8204
   3.250   0.5810   0.02598   0.01764  -0.0616   0.6657   0.8253
   3.500   0.6233   0.02520   0.01685  -0.0634   0.6628   0.8287
   4.000   0.6634   0.02518   0.01688  -0.0611   0.6475   0.8378
   4.500   0.7057   0.02511   0.01688  -0.0591   0.6316   0.8481
   5.000   0.7484   0.02493   0.01678  -0.0570   0.6149   0.8581
   5.250   0.7553   0.02559   0.01751  -0.0545   0.6016   0.8653
   5.500   0.7661   0.02600   0.01799  -0.0523   0.5890   0.8719
   5.750   0.7871   0.02598   0.01802  -0.0514   0.5780   0.8786
   6.000   0.8155   0.02552   0.01759  -0.0511   0.5685   0.8849
   6.500   0.8517   0.02570   0.01788  -0.0484   0.5395   0.9031
   6.750   0.8751   0.02553   0.01773  -0.0476   0.5241   0.9141
   7.250   0.9321   0.02490   0.01706  -0.0475   0.4875   0.9452
   7.500   0.9580   0.02485   0.01695  -0.0476   0.4649   1.0000
   7.750   0.9851   0.02499   0.01694  -0.0479   0.4422   1.0000
   8.000   1.0072   0.02547   0.01730  -0.0477   0.4202   1.0000
   8.250   1.0266   0.02612   0.01782  -0.0473   0.3988   1.0000
   8.500   1.0446   0.02686   0.01843  -0.0467   0.3793   1.0000
   8.750   1.0616   0.02767   0.01914  -0.0461   0.3617   1.0000
   9.000   1.0777   0.02854   0.01993  -0.0454   0.3454   1.0000
   9.250   1.0930   0.02946   0.02078  -0.0447   0.3303   1.0000
   9.500   1.1083   0.03040   0.02168  -0.0439   0.3166   1.0000
   9.750   1.1236   0.03136   0.02259  -0.0432   0.3042   1.0000
  10.000   1.1387   0.03232   0.02349  -0.0425   0.2929   1.0000
  10.250   1.1531   0.03334   0.02449  -0.0417   0.2820   1.0000
  10.500   1.1679   0.03436   0.02553  -0.0410   0.2720   1.0000
  10.750   1.1819   0.03541   0.02651  -0.0402   0.2629   1.0000
  11.000   1.1957   0.03651   0.02769  -0.0395   0.2535   1.0000
  11.250   1.2096   0.03760   0.02874  -0.0388   0.2457   1.0000
  11.500   1.2225   0.03878   0.02999  -0.0381   0.2372   1.0000
  11.750   1.2357   0.03994   0.03114  -0.0374   0.2300   1.0000
  12.000   1.2479   0.04121   0.03250  -0.0367   0.2223   1.0000
  12.250   1.2605   0.04243   0.03367  -0.0360   0.2159   1.0000
  12.500   1.2717   0.04381   0.03519  -0.0354   0.2086   1.0000
  12.750   1.2824   0.04520   0.03659  -0.0347   0.2023   1.0000
  13.000   1.2932   0.04664   0.03813  -0.0341   0.1959   1.0000
  13.250   1.3027   0.04818   0.03974  -0.0334   0.1897   1.0000
  13.500   1.3128   0.04969   0.04126  -0.0328   0.1842   1.0000
  13.750   1.3212   0.05142   0.04315  -0.0323   0.1781   1.0000
  14.000   1.3291   0.05315   0.04492  -0.0318   0.1728   1.0000
  14.250   1.3374   0.05493   0.04678  -0.0313   0.1677   1.0000
  14.500   1.3433   0.05695   0.04894  -0.0309   0.1621   1.0000
  14.750   1.3500   0.05887   0.05088  -0.0305   0.1574   1.0000
  15.000   1.3558   0.06102   0.05317  -0.0302   0.1526   1.0000
  15.250   1.3597   0.06337   0.05566  -0.0299   0.1476   1.0000
  15.500   1.3643   0.06561   0.05792  -0.0297   0.1433   1.0000
  15.750   1.3677   0.06813   0.06060  -0.0297   0.1390   1.0000
  16.000   1.3693   0.07092   0.06356  -0.0297   0.1345   1.0000
  16.250   1.3713   0.07362   0.06632  -0.0298   0.1305   1.0000
  16.500   1.3737   0.07636   0.06911  -0.0300   0.1268   1.0000
  16.750   1.3715   0.07982   0.07280  -0.0305   0.1227   1.0000
  17.000   1.3705   0.08313   0.07623  -0.0311   0.1190   1.0000
  17.250   1.3723   0.08602   0.07914  -0.0316   0.1157   1.0000
  17.500   1.3680   0.09000   0.08331  -0.0325   0.1122   1.0000
  17.750   1.3622   0.09426   0.08778  -0.0337   0.1088   1.0000
  18.000   1.3585   0.09823   0.09186  -0.0350   0.1056   1.0000
  18.250   1.3600   0.10134   0.09498  -0.0360   0.1027   1.0000
  18.500   1.3509   0.10637   0.10022  -0.0379   0.0999   1.0000
  18.750   1.3388   0.11204   0.10611  -0.0402   0.0970   1.0000
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