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EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 583 AIRFOIL (e583-il)
Reynolds number: 50,000
Max Cl/Cd: 11.49 at α=11.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e583-il-50000-n5.txt
Download as CSV file: xf-e583-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 583 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0876   0.12072   0.11455  -0.0832   0.9310   0.1045
 -11.250  -0.0810   0.11676   0.11058  -0.0856   0.9257   0.1024
 -10.750  -0.2013   0.11523   0.10877  -0.0791   0.9478   0.0490
 -10.500  -0.1891   0.11085   0.10437  -0.0826   0.9413   0.0479
 -10.250  -0.1801   0.10626   0.09978  -0.0866   0.9343   0.0473
  -9.750  -0.1799   0.09327   0.08680  -0.0990   0.9204   0.0426
  -9.500  -0.1729   0.08756   0.08106  -0.1047   0.9149   0.0425
  -9.250  -0.1690   0.08338   0.07686  -0.1078   0.9065   0.0419
  -9.000  -0.1695   0.07809   0.07151  -0.1127   0.8996   0.0416
  -8.750  -0.1766   0.07446   0.06782  -0.1146   0.8900   0.0411
  -8.500  -0.1865   0.07045   0.06369  -0.1164   0.8822   0.0407
  -8.250  -0.2062   0.06811   0.06127  -0.1143   0.8711   0.0406
  -8.000  -0.2126   0.06473   0.05768  -0.1143   0.8649   0.0402
  -7.750  -0.2287   0.06296   0.05578  -0.1108   0.8550   0.0401
  -7.500  -0.2313   0.05990   0.05244  -0.1098   0.8493   0.0399
  -7.250  -0.2424   0.05814   0.05047  -0.1061   0.8407   0.0400
  -6.750  -0.2347   0.05255   0.04412  -0.1031   0.8307   0.0404
  -6.500  -0.2430   0.05135   0.04268  -0.0985   0.8224   0.0404
  -6.250  -0.2321   0.04882   0.03970  -0.0970   0.8179   0.0406
  -6.000  -0.2122   0.04608   0.03643  -0.0965   0.8148   0.0412
  -5.750  -0.2152   0.04530   0.03540  -0.0921   0.8071   0.0415
  -5.500  -0.1980   0.04347   0.03314  -0.0907   0.8029   0.0431
  -5.250  -0.1733   0.04207   0.03160  -0.0907   0.7999   0.0462
  -5.000  -0.1525   0.04077   0.02991  -0.0895   0.7960   0.0493
  -4.750  -0.1460   0.04020   0.02917  -0.0862   0.7896   0.0511
  -4.500  -0.1216   0.03918   0.02807  -0.0857   0.7860   0.0553
  -4.250  -0.0903   0.03806   0.02681  -0.0859   0.7834   0.0626
  -4.000  -0.0564   0.03700   0.02562  -0.0864   0.7813   0.0735
  -3.750  -0.0649   0.03747   0.02606  -0.0810   0.7733   0.0782
  -3.250  -0.0213   0.03592   0.02458  -0.0791   0.7666   0.1256
  -3.000  -0.0137   0.03542   0.02437  -0.0764   0.7619   0.1653
  -2.750  -0.0185   0.03522   0.02455  -0.0720   0.7552   0.2220
  -2.500  -0.0181   0.03347   0.02453  -0.0676   0.7514   0.4935
  -2.250  -0.0084   0.03460   0.02626  -0.0592   0.7488   0.7773
  -2.000  -0.0227   0.03577   0.02736  -0.0522   0.7410   0.8130
  -1.750   0.2301   0.03672   0.02700  -0.0837   0.7499   0.9513
  -1.500   0.2948   0.03639   0.02627  -0.0910   0.7484   0.9644
  -1.250   0.3030   0.03734   0.02713  -0.0898   0.7406   0.9755
  -1.000   0.3356   0.03750   0.02708  -0.0918   0.7365   0.9830
  -0.750   0.3771   0.03738   0.02673  -0.0951   0.7337   0.9881
  -0.500   0.4179   0.03723   0.02636  -0.0981   0.7316   0.9927
  -0.250   0.4083   0.03873   0.02786  -0.0943   0.7220   1.0000
   0.000   0.4233   0.03898   0.02799  -0.0927   0.7179   1.0000
   0.250   0.4293   0.03949   0.02840  -0.0899   0.7131   1.0000
   0.500   0.3985   0.04085   0.02979  -0.0817   0.7036   1.0000
   0.750   0.4189   0.04097   0.02978  -0.0809   0.7002   1.0000
   1.250   0.3969   0.04278   0.03152  -0.0706   0.6857   1.0000
   1.500   0.4204   0.04282   0.03145  -0.0701   0.6828   1.0000
   1.750   0.3840   0.04431   0.03297  -0.0618   0.6720   1.0000
   2.000   0.4009   0.04450   0.03307  -0.0604   0.6682   1.0000
   2.250   0.3844   0.04548   0.03403  -0.0548   0.6600   1.0000
   2.500   0.3886   0.04597   0.03446  -0.0519   0.6542   1.0000
   2.750   0.4101   0.04607   0.03447  -0.0510   0.6508   1.0000
   3.000   0.3891   0.04727   0.03565  -0.0453   0.6411   1.0000
   3.250   0.4067   0.04762   0.03593  -0.0442   0.6366   1.0000
   3.500   0.4349   0.04775   0.03599  -0.0443   0.6337   1.0000
   3.750   0.4222   0.04932   0.03754  -0.0407   0.6231   1.0000
   4.000   0.4487   0.04965   0.03781  -0.0408   0.6194   1.0000
   4.250   0.4510   0.05097   0.03912  -0.0390   0.6107   1.0000
   4.500   0.4721   0.05161   0.03973  -0.0389   0.6053   1.0000
   4.750   0.5033   0.05184   0.03992  -0.0395   0.6022   1.0000
   5.000   0.5011   0.05356   0.04164  -0.0377   0.5916   1.0000
   5.250   0.5296   0.05394   0.04201  -0.0382   0.5876   1.0000
   5.500   0.5339   0.05549   0.04357  -0.0370   0.5784   1.0000
   5.750   0.5584   0.05606   0.04415  -0.0372   0.5731   1.0000
   6.250   0.5891   0.05818   0.04630  -0.0365   0.5587   1.0000
   6.500   0.6211   0.05832   0.04646  -0.0371   0.5552   1.0000
   6.750   0.6207   0.06031   0.04852  -0.0359   0.5441   1.0000
   7.000   0.6516   0.06047   0.04870  -0.0364   0.5403   1.0000
   7.250   0.6527   0.06247   0.05075  -0.0353   0.5294   1.0000
   7.500   0.6830   0.06259   0.05092  -0.0357   0.5252   1.0000
   7.750   0.6846   0.06466   0.05305  -0.0349   0.5144   1.0000
   8.000   0.7147   0.06472   0.05320  -0.0352   0.5101   1.0000
   8.250   0.7163   0.06688   0.05543  -0.0344   0.4991   1.0000
   8.500   0.7470   0.06682   0.05544  -0.0346   0.4948   1.0000
   8.750   0.7480   0.06909   0.05781  -0.0339   0.4834   1.0000
   9.000   0.7794   0.06890   0.05771  -0.0341   0.4793   1.0000
   9.250   0.7794   0.07132   0.06021  -0.0334   0.4675   1.0000
   9.500   0.8117   0.07096   0.05998  -0.0336   0.4636   1.0000
   9.750   0.8109   0.07353   0.06264  -0.0330   0.4514   1.0000
  10.000   0.8395   0.07340   0.06263  -0.0329   0.4467   1.0000
  10.250   0.8420   0.07575   0.06508  -0.0325   0.4352   1.0000
  10.750   0.8734   0.07787   0.06745  -0.0320   0.4188   1.0000
  11.250   0.9053   0.07981   0.06965  -0.0314   0.4024   1.0000
  11.750   0.9374   0.08161   0.07175  -0.0307   0.3861   1.0000
  12.000   0.9339   0.08495   0.07520  -0.0307   0.3732   1.0000
  12.500   0.9653   0.08672   0.07728  -0.0300   0.3564   1.0000
  13.000   0.9978   0.08814   0.07902  -0.0292   0.3399   1.0000
  13.250   0.9923   0.09205   0.08304  -0.0296   0.3269   1.0000
  13.750   1.0256   0.09322   0.08455  -0.0288   0.3101   1.0000
  14.000   1.0196   0.09740   0.08884  -0.0294   0.2975   1.0000
  14.250   1.0543   0.09501   0.08665  -0.0282   0.2919   1.0000
  14.500   1.0542   0.09819   0.08998  -0.0285   0.2802   1.0000
  14.750   1.0479   0.10254   0.09445  -0.0294   0.2679   1.0000
  15.000   1.1007   0.09687   0.08899  -0.0270   0.2629   1.0000
  15.500   1.0771   0.10742   0.09976  -0.0295   0.2381   1.0000
  15.750   1.1009   0.10653   0.09903  -0.0287   0.2293   1.0000
  16.000   1.1214   0.10614   0.09877  -0.0280   0.2192   1.0000
  16.250   1.1036   0.11273   0.10548  -0.0301   0.2079   1.0000
  16.500   1.1113   0.11470   0.10755  -0.0304   0.1978   1.0000
  16.750   1.1436   0.11200   0.10491  -0.0288   0.1873   1.0000
  17.000   1.1287   0.11818   0.11123  -0.0311   0.1772   1.0000
  17.250   1.1195   0.12346   0.11664  -0.0330   0.1678   1.0000
  17.500   1.1394   0.12294   0.11615  -0.0324   0.1575   1.0000
  17.750   1.1400   0.12626   0.11955  -0.0337   0.1479   1.0000
  18.000   1.1205   0.13388   0.12730  -0.0371   0.1403   1.0000
  18.250   1.1394   0.13342   0.12685  -0.0366   0.1306   1.0000
  18.500   1.1134   0.14277   0.13636  -0.0412   0.1242   1.0000
  18.750   1.1222   0.14449   0.13811  -0.0420   0.1163   1.0000
  19.000   1.1064   0.15190   0.14563  -0.0459   0.1099   1.0000
  19.250   1.1050   0.15613   0.14990  -0.0481   0.1037   1.0000
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