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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 200,000
Max Cl/Cd: 77.97 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e582-il-200000.txt
Download as CSV file: xf-e582-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0969   0.11331   0.11003  -0.0847   0.9653   0.0362
 -11.500  -0.0989   0.10917   0.10589  -0.0896   0.9628   0.0371
 -11.250  -0.0984   0.10458   0.10130  -0.0946   0.9608   0.0374
 -11.000  -0.0826   0.09915   0.09588  -0.0959   0.9594   0.0382
 -10.750  -0.0663   0.09573   0.09245  -0.0969   0.9552   0.0392
 -10.500  -0.0540   0.09192   0.08862  -0.0991   0.9516   0.0404
 -10.250  -0.0438   0.08764   0.08433  -0.1022   0.9489   0.0421
 -10.000  -0.0351   0.08296   0.07964  -0.1061   0.9466   0.0436
  -9.750  -0.0441   0.07704   0.07374  -0.1133   0.9418   0.0461
  -9.500  -0.0474   0.07145   0.06815  -0.1192   0.9361   0.0464
  -9.250  -0.0556   0.06420   0.06086  -0.1280   0.9319   0.0465
  -9.000  -0.0181   0.06238   0.05906  -0.1215   0.9304   0.0489
  -8.750  -0.0125   0.05910   0.05577  -0.1226   0.9226   0.0509
  -8.500  -0.0103   0.05418   0.05084  -0.1269   0.9173   0.0526
  -8.250  -0.0211   0.04903   0.04566  -0.1312   0.9086   0.0529
  -8.000  -0.1124   0.05759   0.05389  -0.1368   0.9104   0.0483
  -7.750  -0.1020   0.05505   0.05130  -0.1373   0.9038   0.0499
  -7.500  -0.0992   0.05250   0.04864  -0.1372   0.8960   0.0515
  -7.250  -0.0978   0.04973   0.04567  -0.1367   0.8883   0.0539
  -7.000  -0.1161   0.04842   0.04366  -0.1332   0.8779   0.0578
  -6.750  -0.0985   0.04396   0.03938  -0.1338   0.8737   0.0597
  -6.500  -0.0785   0.02939   0.02461  -0.1250   0.8555   0.0699
  -6.250  -0.0656   0.02487   0.02040  -0.1256   0.8518   0.0736
  -6.000  -0.0555   0.02318   0.01860  -0.1240   0.8458   0.0785
  -5.750  -0.0456   0.02042   0.01551  -0.1229   0.8416   0.0867
  -5.500  -0.0364   0.02658   0.01957  -0.1231   0.8468   0.0307
  -5.250  -0.0102   0.02481   0.01756  -0.1227   0.8431   0.0293
  -5.000   0.0180   0.02282   0.01529  -0.1226   0.8403   0.0285
  -4.750   0.0386   0.02163   0.01392  -0.1211   0.8354   0.0283
  -4.500   0.0618   0.02057   0.01271  -0.1199   0.8306   0.0288
  -4.250   0.0894   0.01963   0.01164  -0.1196   0.8272   0.0299
  -4.000   0.1158   0.01845   0.01050  -0.1194   0.8245   0.0328
  -3.750   0.1320   0.01811   0.01017  -0.1174   0.8188   0.0383
  -3.500   0.1530   0.01740   0.00953  -0.1164   0.8143   0.0503
  -3.250   0.1761   0.01621   0.00870  -0.1159   0.8110   0.1259
  -3.000   0.1921   0.01437   0.00832  -0.1154   0.8076   0.4589
  -2.750   0.1918   0.01468   0.00972  -0.1082   0.8012   0.7409
  -2.500   0.2119   0.01541   0.01033  -0.1052   0.7974   0.7911
  -2.250   0.2337   0.01593   0.01072  -0.1026   0.7946   0.8170
  -2.000   0.2452   0.01649   0.01123  -0.0981   0.7898   0.8344
  -1.750   0.2569   0.01689   0.01158  -0.0939   0.7846   0.8505
  -1.500   0.2758   0.01710   0.01169  -0.0908   0.7812   0.8665
  -1.250   0.3008   0.01718   0.01165  -0.0890   0.7787   0.8814
  -1.000   0.3087   0.01745   0.01190  -0.0849   0.7726   0.8939
  -0.750   0.3326   0.01756   0.01194  -0.0829   0.7686   0.9111
  -0.500   0.3880   0.01761   0.01186  -0.0870   0.7665   0.9333
  -0.250   0.4685   0.01740   0.01147  -0.0975   0.7650   0.9377
   0.000   0.5128   0.01722   0.01115  -0.1010   0.7627   0.9412
   0.250   0.5141   0.01745   0.01143  -0.0964   0.7555   0.9479
   0.500   0.5533   0.01731   0.01121  -0.0990   0.7518   0.9501
   0.750   0.5921   0.01712   0.01092  -0.1015   0.7489   0.9522
   1.000   0.6103   0.01723   0.01102  -0.1001   0.7437   0.9559
   1.250   0.6178   0.01731   0.01110  -0.0965   0.7379   0.9600
   1.500   0.6567   0.01710   0.01083  -0.0990   0.7346   0.9611
   1.750   0.6936   0.01697   0.01063  -0.1011   0.7311   0.9624
   2.000   0.7089   0.01713   0.01085  -0.0993   0.7241   0.9653
   2.250   0.7398   0.01698   0.01065  -0.1002   0.7200   0.9669
   2.500   0.7756   0.01679   0.01040  -0.1019   0.7169   0.9680
   2.750   0.7721   0.01708   0.01078  -0.0964   0.7090   0.9719
   3.000   0.8051   0.01691   0.01058  -0.0977   0.7047   0.9730
   3.250   0.8429   0.01670   0.01030  -0.0998   0.7015   0.9734
   3.500   0.8569   0.01691   0.01063  -0.0978   0.6933   0.9760
   3.750   0.8911   0.01669   0.01039  -0.0993   0.6888   0.9770
   4.000   0.9148   0.01667   0.01038  -0.0988   0.6830   0.9786
   4.250   0.9348   0.01666   0.01041  -0.0977   0.6762   0.9806
   4.500   0.9712   0.01638   0.01012  -0.0994   0.6717   0.9816
   4.750   0.9838   0.01652   0.01035  -0.0970   0.6637   0.9844
   5.000   1.0177   0.01629   0.01011  -0.0984   0.6581   0.9851
   5.250   1.0413   0.01630   0.01021  -0.0980   0.6504   0.9870
   5.500   1.0719   0.01611   0.01004  -0.0988   0.6436   0.9884
   5.750   1.0966   0.01610   0.01009  -0.0986   0.6355   0.9910
   6.000   1.1269   0.01590   0.00992  -0.0993   0.6280   0.9928
   6.250   1.1472   0.01593   0.01004  -0.0983   0.6185   0.9958
   6.500   1.1787   0.01575   0.00986  -0.0992   0.6103   0.9976
   6.750   1.1897   0.01578   0.00998  -0.0963   0.5999   1.0000
   7.000   1.1916   0.01578   0.01004  -0.0915   0.5905   1.0000
   7.250   1.2069   0.01567   0.00990  -0.0893   0.5811   1.0000
   7.500   1.2112   0.01574   0.01005  -0.0852   0.5694   1.0000
   7.750   1.2261   0.01584   0.01022  -0.0832   0.5567   1.0000
   8.000   1.2426   0.01596   0.01038  -0.0815   0.5432   1.0000
   8.250   1.2592   0.01615   0.01059  -0.0800   0.5282   1.0000
   8.500   1.2758   0.01641   0.01086  -0.0784   0.5118   1.0000
   8.750   1.2919   0.01675   0.01121  -0.0769   0.4941   1.0000
   9.000   1.3060   0.01721   0.01165  -0.0752   0.4752   1.0000
   9.250   1.3173   0.01781   0.01226  -0.0732   0.4551   1.0000
   9.500   1.3281   0.01851   0.01292  -0.0712   0.4344   1.0000
   9.750   1.3367   0.01935   0.01372  -0.0690   0.4130   1.0000
  10.000   1.3435   0.02033   0.01467  -0.0667   0.3911   1.0000
  10.250   1.3489   0.02146   0.01574  -0.0644   0.3694   1.0000
  10.500   1.3530   0.02272   0.01696  -0.0621   0.3475   1.0000
  10.750   1.3558   0.02414   0.01829  -0.0597   0.3269   1.0000
  11.000   1.3588   0.02562   0.01975  -0.0577   0.3055   1.0000
  11.250   1.3604   0.02727   0.02134  -0.0556   0.2852   1.0000
  11.500   1.3616   0.02902   0.02304  -0.0536   0.2661   1.0000
  11.750   1.3634   0.03082   0.02483  -0.0518   0.2465   1.0000
  12.000   1.3640   0.03277   0.02674  -0.0501   0.2279   1.0000
  12.250   1.3641   0.03485   0.02877  -0.0485   0.2104   1.0000
  12.500   1.3644   0.03701   0.03089  -0.0471   0.1936   1.0000
  12.750   1.3655   0.03919   0.03307  -0.0458   0.1770   1.0000
  13.000   1.3657   0.04153   0.03540  -0.0446   0.1605   1.0000
  13.250   1.3652   0.04401   0.03786  -0.0436   0.1451   1.0000
  13.500   1.3642   0.04665   0.04047  -0.0426   0.1304   1.0000
  13.750   1.3623   0.04946   0.04326  -0.0418   0.1163   1.0000
  14.000   1.3600   0.05240   0.04620  -0.0411   0.1031   1.0000
  14.250   1.3571   0.05552   0.04931  -0.0406   0.0910   1.0000
  14.500   1.3537   0.05880   0.05260  -0.0402   0.0799   1.0000
  14.750   1.3496   0.06228   0.05608  -0.0399   0.0705   1.0000
  15.000   1.3428   0.06614   0.05990  -0.0397   0.0630   1.0000
  15.250   1.3409   0.06958   0.06342  -0.0398   0.0558   1.0000
  15.500   1.3365   0.07338   0.06727  -0.0399   0.0501   1.0000
  15.750   1.3317   0.07734   0.07126  -0.0403   0.0452   1.0000
  16.000   1.3285   0.08116   0.07518  -0.0407   0.0406   1.0000
  16.250   1.3243   0.08523   0.07930  -0.0415   0.0369   1.0000
  16.500   1.3201   0.08935   0.08351  -0.0422   0.0333   1.0000
  16.750   1.3170   0.09345   0.08770  -0.0432   0.0302   1.0000
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