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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 50,000
Max Cl/Cd: 20.68 at α=11.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e582-il-50000-n5.txt
Download as CSV file: xf-e582-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3138   0.14107   0.13462  -0.0440   1.0000   0.0928
 -11.000  -0.3259   0.13994   0.13359  -0.0424   1.0000   0.0946
 -10.750  -0.3384   0.13860   0.13235  -0.0445   0.9977   0.0968
 -10.500  -0.3382   0.13522   0.12901  -0.0505   0.9917   0.0975
 -10.000  -0.3140   0.12591   0.11972  -0.0566   0.9821   0.0984
  -9.750  -0.2894   0.11863   0.11230  -0.0579   0.9780   0.0657
  -9.250  -0.2860   0.10711   0.10079  -0.0679   0.9655   0.0458
  -9.000  -0.2759   0.10310   0.09678  -0.0706   0.9605   0.0449
  -8.750  -0.2725   0.09916   0.09285  -0.0732   0.9538   0.0443
  -8.500  -0.2688   0.09488   0.08859  -0.0767   0.9476   0.0436
  -8.250  -0.2700   0.09060   0.08433  -0.0798   0.9406   0.0426
  -8.000  -0.2750   0.08599   0.07973  -0.0837   0.9331   0.0419
  -7.500  -0.3108   0.07538   0.06878  -0.0891   0.9149   0.0373
  -7.250  -0.3209   0.07254   0.06582  -0.0877   0.9059   0.0373
  -7.000  -0.3149   0.06862   0.06168  -0.0891   0.9010   0.0372
  -6.750  -0.3227   0.06613   0.05901  -0.0867   0.8925   0.0372
  -6.500  -0.3146   0.06262   0.05522  -0.0871   0.8875   0.0371
  -6.250  -0.3125   0.05962   0.05187  -0.0857   0.8811   0.0373
  -6.000  -0.3061   0.05663   0.04847  -0.0846   0.8750   0.0375
  -5.750  -0.2877   0.05337   0.04490  -0.0852   0.8713   0.0378
  -5.500  -0.2792   0.05109   0.04230  -0.0834   0.8653   0.0380
  -5.250  -0.2634   0.04864   0.03947  -0.0826   0.8601   0.0381
  -5.000  -0.2384   0.04611   0.03651  -0.0831   0.8567   0.0386
  -4.750  -0.2164   0.04411   0.03418  -0.0828   0.8527   0.0394
  -4.500  -0.2020   0.04279   0.03261  -0.0810   0.8468   0.0412
  -4.250  -0.1748   0.04119   0.03059  -0.0811   0.8430   0.0443
  -4.000  -0.1429   0.03948   0.02852  -0.0816   0.8403   0.0478
  -3.750  -0.1272   0.03865   0.02758  -0.0796   0.8348   0.0506
  -3.500  -0.1045   0.03786   0.02655  -0.0784   0.8301   0.0562
  -3.250  -0.0763   0.03693   0.02557  -0.0782   0.8268   0.0644
  -3.000  -0.0448   0.03594   0.02445  -0.0784   0.8242   0.0808
  -2.750  -0.0379   0.03573   0.02423  -0.0753   0.8171   0.0951
  -2.500  -0.0159   0.03479   0.02352  -0.0746   0.8128   0.1362
  -2.250   0.0061   0.03282   0.02274  -0.0749   0.8098   0.3114
  -2.000  -0.0120   0.03251   0.02438  -0.0633   0.8033   0.6514
  -1.750  -0.0071   0.03328   0.02489  -0.0579   0.7976   0.8175
  -1.500   0.2464   0.03389   0.02417  -0.0922   0.8096   0.9916
  -1.250   0.2698   0.03428   0.02434  -0.0930   0.8030   1.0000
  -1.000   0.2817   0.03452   0.02441  -0.0911   0.7970   1.0000
  -0.750   0.3094   0.03450   0.02416  -0.0916   0.7936   1.0000
  -0.500   0.2932   0.03528   0.02489  -0.0851   0.7836   1.0000
  -0.250   0.3163   0.03536   0.02479  -0.0848   0.7794   1.0000
   0.000   0.3067   0.03602   0.02539  -0.0795   0.7705   1.0000
   0.250   0.3239   0.03621   0.02543  -0.0782   0.7654   1.0000
   0.500   0.3259   0.03668   0.02581  -0.0747   0.7582   1.0000
   0.750   0.3327   0.03705   0.02610  -0.0718   0.7515   1.0000
   1.000   0.3586   0.03711   0.02602  -0.0718   0.7478   1.0000
   1.250   0.3429   0.03786   0.02674  -0.0657   0.7376   1.0000
   1.500   0.3661   0.03797   0.02673  -0.0652   0.7334   1.0000
   1.750   0.3558   0.03865   0.02738  -0.0600   0.7239   1.0000
   2.000   0.3766   0.03883   0.02746  -0.0591   0.7191   1.0000
   2.250   0.3777   0.03946   0.02804  -0.0558   0.7106   1.0000
   2.500   0.3973   0.03979   0.02830  -0.0550   0.7048   1.0000
   2.750   0.4253   0.03997   0.02840  -0.0554   0.7007   1.0000
   3.000   0.4285   0.04086   0.02927  -0.0529   0.6907   1.0000
   3.250   0.4606   0.04099   0.02934  -0.0537   0.6869   1.0000
   3.500   0.4656   0.04202   0.03036  -0.0517   0.6766   1.0000
   3.750   0.4973   0.04218   0.03048  -0.0526   0.6723   1.0000
   4.000   0.5058   0.04323   0.03153  -0.0511   0.6624   1.0000
   4.250   0.5372   0.04340   0.03168  -0.0519   0.6576   1.0000
   4.500   0.5476   0.04446   0.03275  -0.0508   0.6477   1.0000
   4.750   0.5790   0.04461   0.03293  -0.0515   0.6428   1.0000
   5.000   0.5901   0.04571   0.03406  -0.0505   0.6326   1.0000
   5.250   0.6223   0.04579   0.03416  -0.0513   0.6277   1.0000
   5.500   0.6328   0.04696   0.03537  -0.0503   0.6170   1.0000
   5.750   0.6671   0.04686   0.03534  -0.0511   0.6124   1.0000
   6.000   0.6766   0.04813   0.03666  -0.0501   0.6009   1.0000
   6.250   0.7128   0.04783   0.03643  -0.0509   0.5969   1.0000
   6.500   0.7215   0.04917   0.03783  -0.0499   0.5848   1.0000
   7.000   0.7675   0.05005   0.03892  -0.0496   0.5685   1.0000
   7.250   0.7788   0.05129   0.04024  -0.0488   0.5568   1.0000
   7.500   0.8148   0.05070   0.03979  -0.0492   0.5523   1.0000
   7.750   0.8243   0.05206   0.04126  -0.0483   0.5397   1.0000
   8.000   0.8375   0.05318   0.04248  -0.0476   0.5282   1.0000
   8.250   0.8724   0.05241   0.04188  -0.0477   0.5229   1.0000
   8.500   0.8828   0.05373   0.04332  -0.0468   0.5102   1.0000
   9.000   0.9322   0.05364   0.04353  -0.0460   0.4931   1.0000
   9.250   0.9432   0.05488   0.04493  -0.0451   0.4802   1.0000
   9.500   0.9575   0.05581   0.04600  -0.0443   0.4682   1.0000
   9.750   0.9972   0.05405   0.04444  -0.0440   0.4625   1.0000
  10.250   1.0232   0.05603   0.04675  -0.0423   0.4362   1.0000
  10.500   1.0409   0.05653   0.04741  -0.0415   0.4240   1.0000
  10.750   1.0690   0.05583   0.04689  -0.0408   0.4132   1.0000
  11.000   1.1025   0.05451   0.04577  -0.0401   0.4021   1.0000
  11.250   1.1189   0.05506   0.04646  -0.0391   0.3876   1.0000
  11.500   1.1365   0.05547   0.04701  -0.0382   0.3727   1.0000
  11.750   1.1545   0.05584   0.04750  -0.0373   0.3573   1.0000
  12.000   1.1689   0.05661   0.04839  -0.0363   0.3411   1.0000
  12.250   1.1771   0.05810   0.04999  -0.0353   0.3246   1.0000
  12.500   1.1841   0.05974   0.05173  -0.0344   0.3079   1.0000
  12.750   1.1908   0.06147   0.05355  -0.0335   0.2914   1.0000
  13.000   1.1967   0.06331   0.05547  -0.0327   0.2750   1.0000
  13.250   1.2015   0.06532   0.05754  -0.0319   0.2590   1.0000
  13.500   1.2050   0.06754   0.05985  -0.0313   0.2434   1.0000
  13.750   1.2071   0.06998   0.06236  -0.0308   0.2281   1.0000
  14.000   1.2078   0.07268   0.06512  -0.0304   0.2134   1.0000
  14.250   1.2073   0.07562   0.06812  -0.0302   0.1991   1.0000
  14.500   1.2058   0.07878   0.07134  -0.0302   0.1856   1.0000
  14.750   1.2037   0.08211   0.07475  -0.0303   0.1727   1.0000
  15.000   1.2011   0.08560   0.07829  -0.0307   0.1603   1.0000
  15.250   1.1987   0.08913   0.08185  -0.0311   0.1487   1.0000
  15.500   1.1971   0.09255   0.08527  -0.0316   0.1377   1.0000
  15.750   1.1922   0.09676   0.08962  -0.0325   0.1275   1.0000
  16.000   1.1869   0.10115   0.09416  -0.0337   0.1182   1.0000
  16.250   1.1849   0.10493   0.09795  -0.0347   0.1095   1.0000
  16.500   1.1806   0.10922   0.10235  -0.0361   0.1013   1.0000
  16.750   1.1750   0.11401   0.10729  -0.0378   0.0943   1.0000
  17.000   1.1759   0.11730   0.11051  -0.0389   0.0872   1.0000
  17.250   1.1663   0.12324   0.11674  -0.0414   0.0821   1.0000
  17.500   1.1663   0.12694   0.12044  -0.0430   0.0762   1.0000
  17.750   1.1584   0.13267   0.12637  -0.0457   0.0722   1.0000
  18.000   1.1473   0.13928   0.13322  -0.0491   0.0688   1.0000
  18.250   1.1557   0.14109   0.13488  -0.0498   0.0635   1.0000
  18.500   1.1376   0.14979   0.14390  -0.0548   0.0620   1.0000
  18.750   1.1154   0.16000   0.15434  -0.0609   0.0612   1.0000
  19.000   1.0857   0.17330   0.16775  -0.0689   0.0613   1.0000
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