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EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1233 AIRFOIL (e1233-il)
Reynolds number: 100,000
Max Cl/Cd: 41.48 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1233-il-100000-n5.txt
Download as CSV file: xf-e1233-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1233 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4378   0.08170   0.07658  -0.0662   1.0000   0.0284
 -11.500  -0.4828   0.07254   0.06731  -0.0709   1.0000   0.0281
 -11.250  -0.5157   0.06719   0.06187  -0.0720   1.0000   0.0279
 -11.000  -0.5511   0.06282   0.05740  -0.0714   1.0000   0.0277
 -10.750  -0.5723   0.05747   0.05177  -0.0746   0.9946   0.0277
 -10.500  -0.5811   0.05238   0.04628  -0.0787   0.9846   0.0278
 -10.250  -0.5869   0.04838   0.04186  -0.0805   0.9726   0.0281
 -10.000  -0.5845   0.04485   0.03790  -0.0811   0.9601   0.0285
  -9.750  -0.5730   0.04203   0.03476  -0.0814   0.9480   0.0289
  -9.500  -0.5550   0.04018   0.03282  -0.0817   0.9362   0.0296
  -9.250  -0.5361   0.03830   0.03078  -0.0819   0.9245   0.0302
  -9.000  -0.5147   0.03638   0.02865  -0.0822   0.9138   0.0312
  -8.750  -0.4886   0.03432   0.02626  -0.0831   0.9053   0.0328
  -8.500  -0.4668   0.03311   0.02503  -0.0830   0.8931   0.0344
  -8.250  -0.4390   0.03168   0.02346  -0.0838   0.8837   0.0364
  -8.000  -0.4107   0.03020   0.02184  -0.0844   0.8734   0.0384
  -7.750  -0.3828   0.02899   0.02057  -0.0850   0.8619   0.0403
  -7.500  -0.3467   0.02764   0.01908  -0.0869   0.8533   0.0436
  -7.250  -0.3174   0.02665   0.01800  -0.0877   0.8402   0.0477
  -7.000  -0.2822   0.02556   0.01687  -0.0896   0.8288   0.0527
  -6.750  -0.2439   0.02451   0.01575  -0.0920   0.8171   0.0594
  -6.500  -0.2126   0.02368   0.01486  -0.0931   0.8026   0.0678
  -6.250  -0.1800   0.02292   0.01400  -0.0943   0.7883   0.0787
  -6.000  -0.1475   0.02222   0.01328  -0.0956   0.7741   0.0913
  -5.750  -0.1167   0.02162   0.01264  -0.0966   0.7598   0.1058
  -5.500  -0.0910   0.02113   0.01212  -0.0965   0.7446   0.1212
  -5.250  -0.0650   0.02065   0.01161  -0.0965   0.7303   0.1382
  -5.000  -0.0379   0.02019   0.01111  -0.0966   0.7170   0.1580
  -4.750  -0.0138   0.01970   0.01066  -0.0962   0.7037   0.1811
  -4.500   0.0079   0.01924   0.01027  -0.0954   0.6905   0.2119
  -4.250   0.0302   0.01868   0.00986  -0.0948   0.6787   0.2581
  -4.000   0.0499   0.01805   0.00949  -0.0939   0.6668   0.3286
  -3.750   0.0677   0.01747   0.00938  -0.0923   0.6555   0.4314
  -3.500   0.0896   0.01747   0.00971  -0.0904   0.6451   0.5306
  -3.250   0.1117   0.01772   0.00999  -0.0886   0.6338   0.5834
  -3.000   0.1377   0.01801   0.01015  -0.0876   0.6242   0.6172
  -2.750   0.1609   0.01824   0.01026  -0.0863   0.6134   0.6425
  -2.500   0.1864   0.01854   0.01039  -0.0854   0.6042   0.6623
  -2.250   0.2096   0.01880   0.01053  -0.0841   0.5942   0.6798
  -2.000   0.2343   0.01914   0.01070  -0.0828   0.5859   0.6946
  -1.750   0.2554   0.01950   0.01100  -0.0808   0.5765   0.7081
  -1.500   0.2788   0.01987   0.01122  -0.0792   0.5688   0.7235
  -1.250   0.2990   0.02014   0.01143  -0.0772   0.5599   0.7385
  -1.000   0.3208   0.02042   0.01160  -0.0753   0.5524   0.7488
  -0.750   0.3440   0.02052   0.01159  -0.0744   0.5449   0.7580
  -0.500   0.3659   0.02064   0.01163  -0.0729   0.5371   0.7643
  -0.250   0.3922   0.02069   0.01148  -0.0728   0.5307   0.7719
   0.000   0.4137   0.02074   0.01150  -0.0717   0.5228   0.7772
   0.250   0.4371   0.02081   0.01147  -0.0708   0.5162   0.7819
   0.500   0.4626   0.02087   0.01140  -0.0705   0.5102   0.7875
   0.750   0.4869   0.02092   0.01138  -0.0703   0.5032   0.7931
   1.000   0.5101   0.02099   0.01136  -0.0693   0.4971   0.7968
   1.250   0.5343   0.02108   0.01136  -0.0688   0.4915   0.8012
   1.500   0.5574   0.02117   0.01141  -0.0682   0.4849   0.8061
   1.750   0.5837   0.02126   0.01140  -0.0683   0.4794   0.8112
   2.000   0.6084   0.02138   0.01141  -0.0677   0.4748   0.8147
   2.250   0.6292   0.02150   0.01157  -0.0666   0.4688   0.8189
   2.500   0.6531   0.02163   0.01165  -0.0662   0.4633   0.8236
   2.750   0.6807   0.02177   0.01167  -0.0666   0.4586   0.8285
   3.000   0.7017   0.02193   0.01182  -0.0654   0.4535   0.8322
   3.250   0.7232   0.02209   0.01201  -0.0645   0.4484   0.8362
   3.500   0.7472   0.02227   0.01214  -0.0641   0.4439   0.8408
   3.750   0.7750   0.02246   0.01222  -0.0645   0.4399   0.8457
   4.000   0.7945   0.02267   0.01247  -0.0632   0.4351   0.8498
   4.250   0.8148   0.02288   0.01272  -0.0621   0.4302   0.8542
   4.500   0.8385   0.02309   0.01290  -0.0617   0.4258   0.8588
   4.750   0.8659   0.02332   0.01305  -0.0621   0.4222   0.8637
   5.000   0.8853   0.02358   0.01335  -0.0608   0.4183   0.8683
   5.250   0.9039   0.02387   0.01372  -0.0596   0.4139   0.8735
   5.500   0.9262   0.02415   0.01400  -0.0591   0.4096   0.8787
   5.750   0.9495   0.02437   0.01419  -0.0585   0.4060   0.8836
   6.000   0.9739   0.02462   0.01441  -0.0582   0.4027   0.8891
   6.250   0.9887   0.02502   0.01494  -0.0565   0.3986   0.8960
   6.500   1.0048   0.02535   0.01534  -0.0548   0.3948   0.9021
   6.750   1.0247   0.02565   0.01567  -0.0539   0.3912   0.9092
   7.000   1.0481   0.02590   0.01592  -0.0535   0.3880   0.9165
   7.250   1.0712   0.02621   0.01623  -0.0531   0.3848   0.9250
   7.500   1.0824   0.02674   0.01693  -0.0510   0.3809   0.9367
   7.750   1.1022   0.02726   0.01757  -0.0504   0.3771   0.9503
   8.000   1.1300   0.02772   0.01808  -0.0514   0.3736   0.9730
   8.250   1.1579   0.02809   0.01843  -0.0522   0.3706   1.0000
   8.500   1.1854   0.02858   0.01889  -0.0530   0.3677   1.0000
   8.750   1.1927   0.02952   0.02001  -0.0510   0.3637   1.0000
   9.000   1.2062   0.03034   0.02092  -0.0499   0.3600   1.0000
   9.250   1.2253   0.03103   0.02166  -0.0495   0.3569   1.0000
   9.500   1.2492   0.03158   0.02221  -0.0497   0.3541   1.0000
   9.750   1.2791   0.03199   0.02257  -0.0507   0.3516   1.0000
  10.000   1.2795   0.03327   0.02403  -0.0480   0.3482   1.0000
  10.250   1.2788   0.03466   0.02558  -0.0453   0.3444   1.0000
  10.500   1.2871   0.03577   0.02678  -0.0439   0.3411   1.0000
  10.750   1.3038   0.03659   0.02763  -0.0433   0.3383   1.0000
  11.000   1.3294   0.03705   0.02809  -0.0436   0.3359   1.0000
  11.250   1.3435   0.03803   0.02912  -0.0428   0.3332   1.0000
  11.500   1.3110   0.04129   0.03266  -0.0383   0.3289   1.0000
  11.750   1.2955   0.04407   0.03560  -0.0358   0.3250   1.0000
  12.000   1.3032   0.04555   0.03715  -0.0351   0.3220   1.0000
  12.250   1.3282   0.04592   0.03753  -0.0352   0.3197   1.0000
  12.500   1.3670   0.04544   0.03701  -0.0362   0.3177   1.0000
  13.000   1.1521   0.07047   0.06267  -0.0319   0.2997   1.0000
  13.250   1.2116   0.06638   0.05856  -0.0313   0.3005   1.0000
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