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EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1233 AIRFOIL (e1233-il)
Reynolds number: 200,000
Max Cl/Cd: 56.61 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1233-il-200000.txt
Download as CSV file: xf-e1233-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4248   0.08243   0.07908  -0.0631   1.0000   0.0379
 -11.000  -0.4266   0.08086   0.07759  -0.0618   1.0000   0.0382
 -10.750  -0.6000   0.05959   0.05547  -0.0726   0.9949   0.0330
 -10.500  -0.5903   0.05542   0.05119  -0.0765   0.9879   0.0326
 -10.250  -0.5958   0.05104   0.04651  -0.0794   0.9772   0.0324
 -10.000  -0.5935   0.04634   0.04142  -0.0816   0.9663   0.0322
  -9.750  -0.5820   0.04210   0.03679  -0.0833   0.9568   0.0319
  -9.500  -0.5654   0.03804   0.03224  -0.0849   0.9483   0.0320
  -9.250  -0.5480   0.03509   0.02890  -0.0850   0.9377   0.0322
  -9.000  -0.5253   0.03240   0.02574  -0.0856   0.9289   0.0328
  -8.750  -0.4932   0.03016   0.02333  -0.0873   0.9227   0.0336
  -8.500  -0.4604   0.02898   0.02219  -0.0887   0.9154   0.0354
  -8.250  -0.4286   0.02728   0.02021  -0.0898   0.9080   0.0371
  -8.000  -0.3890   0.02540   0.01825  -0.0922   0.9044   0.0387
  -7.750  -0.3598   0.02419   0.01700  -0.0925   0.8931   0.0404
  -7.500  -0.3150   0.02265   0.01529  -0.0956   0.8882   0.0429
  -7.250  -0.2801   0.02149   0.01422  -0.0972   0.8761   0.0460
  -7.000  -0.2290   0.02028   0.01300  -0.1020   0.8680   0.0519
  -6.750  -0.1824   0.01917   0.01188  -0.1059   0.8551   0.0590
  -6.500  -0.1407   0.01826   0.01090  -0.1090   0.8390   0.0702
  -6.250  -0.1052   0.01745   0.01013  -0.1110   0.8211   0.0847
  -6.000  -0.0739   0.01693   0.00951  -0.1119   0.8027   0.1010
  -5.750  -0.0482   0.01641   0.00899  -0.1119   0.7847   0.1160
  -5.500  -0.0244   0.01602   0.00858  -0.1114   0.7672   0.1316
  -5.250  -0.0018   0.01566   0.00819  -0.1107   0.7507   0.1489
  -5.000   0.0208   0.01531   0.00782  -0.1099   0.7356   0.1705
  -4.750   0.0421   0.01487   0.00743  -0.1090   0.7214   0.1995
  -4.500   0.0596   0.01432   0.00706  -0.1075   0.7067   0.2457
  -4.250   0.0758   0.01349   0.00666  -0.1061   0.6934   0.3444
  -4.000   0.0931   0.01277   0.00660  -0.1045   0.6816   0.5063
  -3.750   0.1142   0.01287   0.00689  -0.1027   0.6686   0.5871
  -3.500   0.1389   0.01318   0.00714  -0.1014   0.6568   0.6257
  -3.250   0.1645   0.01356   0.00741  -0.1003   0.6455   0.6502
  -3.000   0.1880   0.01392   0.00769  -0.0988   0.6338   0.6684
  -2.750   0.2142   0.01432   0.00792  -0.0979   0.6238   0.6837
  -2.500   0.2379   0.01460   0.00810  -0.0967   0.6129   0.6982
  -2.250   0.2623   0.01506   0.00847  -0.0951   0.6036   0.7070
  -2.000   0.2858   0.01528   0.00859  -0.0939   0.5934   0.7189
  -1.750   0.3097   0.01570   0.00891  -0.0923   0.5848   0.7269
  -1.500   0.3330   0.01587   0.00901  -0.0911   0.5753   0.7379
  -1.250   0.3566   0.01632   0.00934  -0.0894   0.5678   0.7458
  -1.000   0.3773   0.01654   0.00955  -0.0875   0.5591   0.7577
  -0.750   0.3979   0.01696   0.00989  -0.0850   0.5518   0.7674
  -0.500   0.4193   0.01714   0.01002  -0.0834   0.5439   0.7774
  -0.250   0.4400   0.01731   0.01014  -0.0814   0.5364   0.7842
   0.000   0.4690   0.01742   0.01007  -0.0821   0.5297   0.7928
   0.250   0.4879   0.01744   0.01012  -0.0799   0.5226   0.7971
   0.500   0.5113   0.01752   0.01012  -0.0789   0.5162   0.8023
   0.750   0.5391   0.01762   0.01009  -0.0793   0.5099   0.8085
   1.000   0.5615   0.01758   0.01005  -0.0784   0.5030   0.8132
   1.250   0.5851   0.01763   0.01001  -0.0775   0.4971   0.8170
   1.500   0.6111   0.01776   0.01006  -0.0773   0.4915   0.8216
   1.750   0.6364   0.01779   0.01007  -0.0772   0.4854   0.8267
   2.000   0.6620   0.01782   0.01004  -0.0770   0.4800   0.8307
   2.250   0.6891   0.01800   0.01009  -0.0769   0.4751   0.8344
   2.500   0.7094   0.01801   0.01017  -0.0757   0.4695   0.8387
   2.750   0.7354   0.01809   0.01020  -0.0757   0.4640   0.8433
   3.000   0.7639   0.01822   0.01023  -0.0762   0.4593   0.8475
   3.250   0.7872   0.01837   0.01037  -0.0754   0.4548   0.8511
   3.500   0.8089   0.01845   0.01050  -0.0745   0.4499   0.8552
   3.750   0.8346   0.01857   0.01058  -0.0744   0.4451   0.8597
   4.000   0.8646   0.01877   0.01068  -0.0753   0.4408   0.8640
   4.250   0.8859   0.01891   0.01085  -0.0742   0.4364   0.8677
   4.500   0.9066   0.01903   0.01102  -0.0731   0.4319   0.8719
   4.750   0.9318   0.01919   0.01117  -0.0729   0.4277   0.8763
   5.000   0.9610   0.01941   0.01132  -0.0736   0.4238   0.8807
   5.250   0.9857   0.01966   0.01154  -0.0733   0.4201   0.8846
   5.500   1.0030   0.01980   0.01178  -0.0716   0.4159   0.8894
   5.750   1.0262   0.01998   0.01200  -0.0711   0.4116   0.8941
   6.000   1.0514   0.02016   0.01216  -0.0710   0.4080   0.8985
   6.250   1.0778   0.02040   0.01234  -0.0710   0.4047   0.9032
   6.500   1.1000   0.02073   0.01273  -0.0704   0.4013   0.9086
   6.750   1.1176   0.02095   0.01306  -0.0689   0.3975   0.9141
   7.000   1.1363   0.02112   0.01328  -0.0675   0.3938   0.9197
   7.250   1.1602   0.02131   0.01347  -0.0672   0.3903   0.9261
   7.500   1.1877   0.02159   0.01369  -0.0675   0.3872   0.9321
   7.750   1.2093   0.02199   0.01416  -0.0668   0.3841   0.9396
   8.000   1.2235   0.02227   0.01459  -0.0648   0.3808   0.9486
   8.250   1.2443   0.02256   0.01498  -0.0641   0.3772   0.9590
   8.500   1.2752   0.02287   0.01531  -0.0654   0.3736   0.9710
   8.750   1.3156   0.02324   0.01563  -0.0685   0.3702   0.9897
   9.000   1.3449   0.02388   0.01629  -0.0697   0.3671   1.0000
   9.250   1.3610   0.02444   0.01702  -0.0687   0.3638   1.0000
   9.500   1.3807   0.02495   0.01762  -0.0683   0.3604   1.0000
   9.750   1.4058   0.02538   0.01807  -0.0686   0.3570   1.0000
  10.000   1.4383   0.02577   0.01843  -0.0702   0.3540   1.0000
  10.250   1.4775   0.02651   0.01910  -0.0731   0.3509   1.0000
  10.500   1.4819   0.02716   0.01995  -0.0700   0.3481   1.0000
  10.750   1.4904   0.02785   0.02078  -0.0677   0.3449   1.0000
  11.000   1.5056   0.02841   0.02141  -0.0664   0.3416   1.0000
  11.250   1.5297   0.02884   0.02184  -0.0665   0.3386   1.0000
  11.500   1.5656   0.02926   0.02220  -0.0685   0.3358   1.0000
  11.750   1.5818   0.03010   0.02311  -0.0675   0.3329   1.0000
  12.000   1.5746   0.03104   0.02424  -0.0628   0.3298   1.0000
  12.250   1.5766   0.03190   0.02524  -0.0598   0.3265   1.0000
  12.500   1.5903   0.03249   0.02587  -0.0584   0.3234   1.0000
  12.750   1.6204   0.03268   0.02602  -0.0592   0.3202   1.0000
  13.000   1.6499   0.03324   0.02655  -0.0602   0.3169   1.0000
  13.250   1.6286   0.03473   0.02828  -0.0544   0.3140   1.0000
  13.500   1.6186   0.03615   0.02987  -0.0506   0.3106   1.0000
  13.750   1.6256   0.03701   0.03080  -0.0489   0.3072   1.0000
  14.000   1.6555   0.03701   0.03075  -0.0495   0.3040   1.0000
  14.250   1.6830   0.03744   0.03116  -0.0501   0.3006   1.0000
  14.500   1.6487   0.04015   0.03414  -0.0446   0.2976   1.0000
  14.750   1.6280   0.04266   0.03683  -0.0413   0.2939   1.0000
  15.000   1.6359   0.04369   0.03791  -0.0403   0.2904   1.0000
  15.250   1.6774   0.04285   0.03698  -0.0415   0.2870   1.0000
  15.500   1.6687   0.04507   0.03933  -0.0395   0.2835   1.0000
  15.750   1.6178   0.05037   0.04491  -0.0360   0.2798   1.0000
  16.000   1.6023   0.05356   0.04822  -0.0348   0.2758   1.0000
  16.250   1.6467   0.05175   0.04632  -0.0354   0.2721   1.0000
  16.500   1.6503   0.05350   0.04813  -0.0348   0.2682   1.0000
  16.750   1.5281   0.06789   0.06295  -0.0337   0.2627   1.0000
  17.000   1.5543   0.06735   0.06241  -0.0337   0.2588   1.0000
  17.250   1.6351   0.06112   0.05599  -0.0335   0.2554   1.0000
  17.500   1.3219   0.10457   0.10005  -0.0424   0.2385   1.0000
  17.750   1.3744   0.09972   0.09523  -0.0409   0.2378   1.0000
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