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EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1200 AIRFOIL (e1200-il)
Reynolds number: 200,000
Max Cl/Cd: 69.51 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1200-il-200000.txt
Download as CSV file: xf-e1200-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.0896   0.10400   0.10050  -0.0976   0.9484   0.0765
 -12.000  -0.1263   0.09601   0.09254  -0.1065   0.9455   0.0813
 -11.750  -0.1171   0.09015   0.08667  -0.1086   0.9428   0.0825
 -11.500  -0.0923   0.08751   0.08399  -0.1093   0.9390   0.0837
 -11.250  -0.0771   0.08458   0.08103  -0.1103   0.9333   0.0854
 -11.000  -0.0684   0.08049   0.07692  -0.1128   0.9290   0.0875
 -10.750  -0.0703   0.07483   0.07124  -0.1168   0.9254   0.0908
 -10.500  -0.3871   0.04859   0.04377  -0.1358   0.9195   0.0495
 -10.250  -0.3857   0.04479   0.03985  -0.1355   0.9122   0.0480
 -10.000  -0.4361   0.03898   0.03307  -0.1295   0.8997   0.0432
  -9.500  -0.4165   0.03523   0.02870  -0.1266   0.8894   0.0422
  -9.250  -0.4064   0.03330   0.02653  -0.1248   0.8837   0.0422
  -9.000  -0.3902   0.03138   0.02434  -0.1239   0.8794   0.0422
  -8.750  -0.3701   0.02978   0.02244  -0.1233   0.8762   0.0423
  -8.500  -0.3540   0.02803   0.02056  -0.1220   0.8716   0.0431
  -8.250  -0.3332   0.02686   0.01937  -0.1214   0.8676   0.0442
  -8.000  -0.3108   0.02597   0.01841  -0.1209   0.8643   0.0455
  -7.750  -0.2856   0.02494   0.01727  -0.1207   0.8615   0.0464
  -7.500  -0.2593   0.02399   0.01620  -0.1205   0.8589   0.0475
  -7.250  -0.2416   0.02341   0.01557  -0.1190   0.8544   0.0485
  -7.000  -0.2207   0.02286   0.01494  -0.1179   0.8508   0.0498
  -6.750  -0.1990   0.02196   0.01407  -0.1171   0.8478   0.0515
  -6.500  -0.1769   0.02138   0.01353  -0.1165   0.8451   0.0545
  -6.250  -0.1531   0.02090   0.01299  -0.1160   0.8428   0.0578
  -6.000  -0.1416   0.02056   0.01268  -0.1136   0.8382   0.0606
  -5.750  -0.1267   0.02019   0.01237  -0.1119   0.8343   0.0651
  -5.500  -0.1088   0.01970   0.01189  -0.1107   0.8311   0.0729
  -5.250  -0.0890   0.01897   0.01131  -0.1098   0.8284   0.0972
  -5.000  -0.0690   0.01802   0.01076  -0.1093   0.8261   0.1698
  -4.750  -0.0600   0.01786   0.01090  -0.1069   0.8213   0.2251
  -4.500  -0.0453   0.01747   0.01086  -0.1056   0.8173   0.3035
  -4.250  -0.0261   0.01670   0.01072  -0.1050   0.8143   0.4365
  -4.000  -0.0018   0.01658   0.01109  -0.1041   0.8120   0.5613
  -3.750   0.0272   0.01691   0.01143  -0.1037   0.8102   0.6172
  -3.500   0.0459   0.01766   0.01220  -0.1017   0.8068   0.6450
  -3.250   0.0569   0.01848   0.01303  -0.0987   0.8012   0.6627
  -3.000   0.0809   0.01897   0.01348  -0.0975   0.7982   0.6782
  -2.750   0.1082   0.01933   0.01381  -0.0967   0.7961   0.6907
  -2.500   0.1379   0.01960   0.01400  -0.0965   0.7943   0.7036
  -2.250   0.1679   0.01987   0.01421  -0.0962   0.7927   0.7140
  -2.000   0.1611   0.02094   0.01534  -0.0908   0.7840   0.7213
  -1.750   0.1860   0.02121   0.01557  -0.0899   0.7811   0.7302
  -1.500   0.2160   0.02129   0.01561  -0.0897   0.7791   0.7387
  -1.250   0.2475   0.02139   0.01565  -0.0897   0.7775   0.7488
  -1.000   0.2427   0.02239   0.01671  -0.0843   0.7694   0.7562
  -0.750   0.2639   0.02268   0.01696  -0.0830   0.7652   0.7670
  -0.500   0.2919   0.02265   0.01693  -0.0821   0.7630   0.7737
  -0.250   0.3276   0.02245   0.01667  -0.0831   0.7614   0.7803
   0.000   0.3663   0.02215   0.01629  -0.0849   0.7600   0.7861
   0.250   0.3524   0.02320   0.01742  -0.0783   0.7489   0.7911
   0.500   0.3899   0.02285   0.01702  -0.0798   0.7468   0.7957
   0.750   0.4337   0.02238   0.01646  -0.0826   0.7453   0.8003
   1.000   0.4738   0.02187   0.01590  -0.0843   0.7437   0.8033
   1.250   0.4687   0.02264   0.01675  -0.0792   0.7331   0.8077
   1.500   0.5111   0.02201   0.01607  -0.0813   0.7307   0.8110
   1.750   0.5579   0.02124   0.01523  -0.0842   0.7286   0.8145
   2.000   0.6059   0.02053   0.01443  -0.0875   0.7266   0.8176
   2.250   0.6074   0.02096   0.01495  -0.0832   0.7167   0.8213
   2.500   0.6464   0.02036   0.01432  -0.0847   0.7135   0.8245
   2.750   0.6891   0.01974   0.01365  -0.0870   0.7111   0.8275
   3.000   0.7041   0.01996   0.01393  -0.0853   0.7028   0.8319
   3.250   0.7385   0.01952   0.01348  -0.0863   0.6983   0.8352
   3.500   0.7777   0.01892   0.01285  -0.0878   0.6952   0.8380
   3.750   0.7940   0.01897   0.01297  -0.0859   0.6873   0.8420
   4.000   0.8275   0.01854   0.01254  -0.0867   0.6819   0.8455
   4.250   0.8711   0.01793   0.01187  -0.0893   0.6781   0.8490
   4.500   0.8823   0.01795   0.01200  -0.0864   0.6685   0.8532
   4.750   0.9187   0.01737   0.01140  -0.0875   0.6631   0.8565
   5.000   0.9365   0.01726   0.01136  -0.0858   0.6535   0.8611
   5.250   0.9740   0.01673   0.01080  -0.0873   0.6467   0.8649
   5.500   0.9866   0.01659   0.01076  -0.0845   0.6354   0.8696
   5.750   1.0079   0.01630   0.01051  -0.0831   0.6248   0.8746
   6.000   1.0342   0.01598   0.01019  -0.0827   0.6132   0.8796
   6.250   1.0530   0.01575   0.00997  -0.0809   0.5989   0.8845
   6.500   1.0639   0.01564   0.00990  -0.0777   0.5817   0.8907
   6.750   1.0746   0.01562   0.00987  -0.0746   0.5618   0.8982
   7.000   1.0850   0.01561   0.00981  -0.0712   0.5390   0.9059
   7.250   1.0953   0.01582   0.00991  -0.0682   0.5121   0.9146
   7.500   1.1025   0.01616   0.01011  -0.0648   0.4839   0.9251
   7.750   1.1069   0.01665   0.01044  -0.0611   0.4563   0.9394
   8.000   1.1154   0.01731   0.01101  -0.0587   0.4282   0.9632
   8.250   1.1293   0.01819   0.01173  -0.0579   0.4015   1.0000
   8.500   1.1423   0.01922   0.01261  -0.0571   0.3787   1.0000
   8.750   1.1557   0.02027   0.01350  -0.0562   0.3593   1.0000
   9.000   1.1691   0.02130   0.01444  -0.0554   0.3416   1.0000
   9.250   1.1824   0.02233   0.01537  -0.0545   0.3262   1.0000
   9.500   1.1958   0.02335   0.01630  -0.0535   0.3124   1.0000
   9.750   1.2093   0.02434   0.01725  -0.0526   0.2994   1.0000
  10.000   1.2235   0.02531   0.01820  -0.0517   0.2881   1.0000
  10.250   1.2375   0.02632   0.01910  -0.0508   0.2780   1.0000
  10.500   1.2509   0.02730   0.02010  -0.0498   0.2678   1.0000
  10.750   1.2648   0.02830   0.02107  -0.0489   0.2587   1.0000
  11.000   1.2782   0.02932   0.02206  -0.0479   0.2499   1.0000
  11.250   1.2919   0.03034   0.02310  -0.0470   0.2416   1.0000
  11.500   1.3051   0.03139   0.02410  -0.0461   0.2336   1.0000
  11.750   1.3183   0.03246   0.02523  -0.0452   0.2260   1.0000
  12.000   1.3307   0.03357   0.02631  -0.0443   0.2188   1.0000
  12.250   1.3438   0.03469   0.02747  -0.0435   0.2117   1.0000
  12.500   1.3549   0.03588   0.02871  -0.0426   0.2049   1.0000
  12.750   1.3683   0.03703   0.02983  -0.0418   0.1984   1.0000
  13.000   1.3778   0.03835   0.03125  -0.0409   0.1919   1.0000
  13.250   1.3928   0.03946   0.03224  -0.0403   0.1855   1.0000
  13.500   1.3997   0.04099   0.03397  -0.0393   0.1797   1.0000
  13.750   1.4090   0.04242   0.03542  -0.0385   0.1741   1.0000
  14.000   1.4204   0.04379   0.03679  -0.0378   0.1684   1.0000
  14.250   1.4270   0.04546   0.03859  -0.0370   0.1628   1.0000
  14.500   1.4372   0.04692   0.04000  -0.0364   0.1575   1.0000
  14.750   1.4443   0.04870   0.04191  -0.0357   0.1523   1.0000
  15.000   1.4499   0.05056   0.04387  -0.0351   0.1472   1.0000
  15.250   1.4622   0.05196   0.04514  -0.0346   0.1420   1.0000
  15.500   1.4638   0.05429   0.04770  -0.0340   0.1377   1.0000
  15.750   1.4682   0.05640   0.04990  -0.0336   0.1331   1.0000
  16.000   1.4795   0.05794   0.05133  -0.0332   0.1283   1.0000
  16.250   1.4797   0.06059   0.05421  -0.0329   0.1245   1.0000
  16.500   1.4821   0.06307   0.05681  -0.0327   0.1203   1.0000
  16.750   1.4876   0.06522   0.05892  -0.0326   0.1161   1.0000
  17.000   1.4895   0.06791   0.06175  -0.0325   0.1123   1.0000
  17.250   1.4891   0.07090   0.06488  -0.0327   0.1085   1.0000
  17.500   1.4895   0.07380   0.06781  -0.0329   0.1047   1.0000
  17.750   1.4933   0.07635   0.07038  -0.0331   0.1010   1.0000
  18.000   1.4893   0.08002   0.07426  -0.0337   0.0976   1.0000
  18.250   1.4874   0.08347   0.07781  -0.0344   0.0943   1.0000
  18.500   1.4895   0.08630   0.08060  -0.0350   0.0908   1.0000
  18.750   1.4849   0.09029   0.08476  -0.0360   0.0878   1.0000
  19.000   1.4796   0.09446   0.08911  -0.0372   0.0849   1.0000
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