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EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 50,000
Max Cl/Cd: 26.71 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e433-il-50000-n5.txt
Download as CSV file: xf-e433-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 433 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3756   0.10697   0.10070  -0.0546   0.9832   0.0441
  -8.500  -0.3721   0.10323   0.09699  -0.0562   0.9784   0.0437
  -8.250  -0.3687   0.09919   0.09296  -0.0589   0.9739   0.0431
  -8.000  -0.3705   0.09514   0.08893  -0.0614   0.9687   0.0425
  -7.750  -0.3773   0.09095   0.08476  -0.0642   0.9626   0.0420
  -7.500  -0.3862   0.08690   0.08071  -0.0664   0.9564   0.0413
  -7.250  -0.3933   0.08273   0.07648  -0.0682   0.9497   0.0405
  -7.000  -0.3956   0.07812   0.07175  -0.0707   0.9440   0.0399
  -6.750  -0.4012   0.07418   0.06766  -0.0711   0.9370   0.0392
  -6.500  -0.3961   0.06955   0.06278  -0.0732   0.9320   0.0391
  -6.250  -0.3963   0.06589   0.05888  -0.0728   0.9258   0.0386
  -6.000  -0.3876   0.06192   0.05457  -0.0735   0.9206   0.0385
  -5.750  -0.3702   0.05778   0.04997  -0.0752   0.9169   0.0385
  -5.500  -0.3605   0.05470   0.04649  -0.0743   0.9114   0.0382
  -5.250  -0.3421   0.05142   0.04273  -0.0746   0.9070   0.0381
  -5.000  -0.3165   0.04841   0.03920  -0.0756   0.9036   0.0383
  -4.750  -0.2886   0.04582   0.03612  -0.0766   0.9007   0.0391
  -4.500  -0.2713   0.04408   0.03402  -0.0754   0.8956   0.0402
  -4.250  -0.2445   0.04227   0.03170  -0.0754   0.8916   0.0433
  -4.000  -0.2150   0.04068   0.02985  -0.0760   0.8885   0.0464
  -3.750  -0.1838   0.03934   0.02828  -0.0764   0.8859   0.0498
  -3.500  -0.1675   0.03857   0.02727  -0.0742   0.8803   0.0540
  -3.250  -0.1432   0.03769   0.02639  -0.0735   0.8761   0.0614
  -3.000  -0.1146   0.03684   0.02544  -0.0735   0.8729   0.0729
  -2.750  -0.0914   0.03611   0.02465  -0.0729   0.8687   0.0904
  -2.500  -0.0728   0.03530   0.02393  -0.0718   0.8632   0.1223
  -2.250  -0.0458   0.03355   0.02310  -0.0732   0.8595   0.2489
  -1.750  -0.0437   0.03314   0.02470  -0.0596   0.8483   0.7809
  -1.500  -0.0383   0.03359   0.02504  -0.0529   0.8432   0.8408
  -1.250  -0.0342   0.03381   0.02514  -0.0462   0.8376   0.8935
  -1.000   0.1185   0.03493   0.02546  -0.0666   0.8416   0.9808
  -0.750   0.1493   0.03514   0.02543  -0.0687   0.8353   0.9893
  -0.500   0.1838   0.03531   0.02535  -0.0711   0.8300   0.9969
  -0.250   0.2158   0.03540   0.02520  -0.0727   0.8261   1.0000
   0.000   0.2110   0.03558   0.02531  -0.0682   0.8165   1.0000
   0.250   0.2332   0.03562   0.02519  -0.0679   0.8115   1.0000
   0.500   0.2308   0.03579   0.02529  -0.0637   0.8021   1.0000
   0.750   0.2517   0.03585   0.02519  -0.0632   0.7967   1.0000
   1.250   0.2756   0.03615   0.02529  -0.0594   0.7819   1.0000
   1.500   0.2857   0.03647   0.02553  -0.0574   0.7733   1.0000
   1.750   0.3121   0.03667   0.02561  -0.0578   0.7674   1.0000
   2.250   0.3567   0.03733   0.02611  -0.0577   0.7529   1.0000
   2.500   0.3786   0.03775   0.02646  -0.0577   0.7452   1.0000
   2.750   0.4054   0.03808   0.02673  -0.0583   0.7382   1.0000
   3.000   0.4288   0.03851   0.02712  -0.0584   0.7304   1.0000
   3.250   0.4564   0.03883   0.02741  -0.0591   0.7231   1.0000
   3.500   0.4787   0.03932   0.02788  -0.0591   0.7145   1.0000
   3.750   0.5087   0.03957   0.02811  -0.0599   0.7076   1.0000
   4.000   0.5289   0.04014   0.02869  -0.0597   0.6980   1.0000
   4.250   0.5625   0.04021   0.02879  -0.0608   0.6919   1.0000
   4.500   0.5802   0.04089   0.02948  -0.0603   0.6810   1.0000
   4.750   0.6173   0.04074   0.02936  -0.0617   0.6759   1.0000
   5.000   0.6335   0.04148   0.03014  -0.0609   0.6641   1.0000
   5.500   0.6883   0.04188   0.03067  -0.0615   0.6471   1.0000
   5.750   0.7063   0.04255   0.03141  -0.0609   0.6354   1.0000
   6.000   0.7451   0.04198   0.03096  -0.0619   0.6304   1.0000
   6.250   0.7612   0.04272   0.03178  -0.0611   0.6176   1.0000
   6.500   0.7799   0.04331   0.03246  -0.0604   0.6056   1.0000
   6.750   0.8190   0.04242   0.03169  -0.0611   0.6004   1.0000
   7.000   0.8357   0.04307   0.03248  -0.0602   0.5873   1.0000
   7.250   0.8548   0.04353   0.03305  -0.0594   0.5747   1.0000
   7.750   0.9150   0.04266   0.03248  -0.0591   0.5559   1.0000
   8.000   0.9345   0.04302   0.03298  -0.0582   0.5424   1.0000
   8.250   0.9560   0.04320   0.03330  -0.0574   0.5291   1.0000
   8.500   0.9800   0.04317   0.03344  -0.0567   0.5161   1.0000
   8.750   1.0064   0.04292   0.03334  -0.0561   0.5029   1.0000
   9.000   1.0333   0.04260   0.03317  -0.0555   0.4888   1.0000
   9.250   1.0583   0.04244   0.03317  -0.0547   0.4734   1.0000
   9.500   1.0817   0.04244   0.03330  -0.0538   0.4566   1.0000
   9.750   1.1046   0.04248   0.03345  -0.0529   0.4387   1.0000
  10.250   1.1469   0.04294   0.03406  -0.0509   0.4004   1.0000
  10.500   1.1586   0.04398   0.03519  -0.0494   0.3802   1.0000
  10.750   1.1732   0.04481   0.03606  -0.0481   0.3600   1.0000
  11.000   1.1857   0.04583   0.03710  -0.0468   0.3402   1.0000
  11.250   1.1921   0.04743   0.03880  -0.0453   0.3205   1.0000
  11.500   1.1995   0.04896   0.04038  -0.0439   0.3013   1.0000
  11.750   1.2069   0.05052   0.04194  -0.0425   0.2827   1.0000
  12.000   1.2113   0.05242   0.04387  -0.0412   0.2647   1.0000
  12.250   1.2138   0.05459   0.04611  -0.0399   0.2473   1.0000
  12.500   1.2159   0.05684   0.04843  -0.0388   0.2306   1.0000
  12.750   1.2175   0.05923   0.05087  -0.0378   0.2148   1.0000
  13.000   1.2188   0.06175   0.05348  -0.0370   0.1999   1.0000
  13.250   1.2193   0.06443   0.05622  -0.0363   0.1858   1.0000
  13.500   1.2195   0.06725   0.05909  -0.0357   0.1726   1.0000
  13.750   1.2191   0.07021   0.06210  -0.0353   0.1603   1.0000
  14.000   1.2189   0.07320   0.06511  -0.0350   0.1490   1.0000
  14.250   1.2175   0.07648   0.06850  -0.0349   0.1382   1.0000
  14.500   1.2152   0.08007   0.07224  -0.0350   0.1282   1.0000
  14.750   1.2144   0.08347   0.07571  -0.0352   0.1194   1.0000
  15.000   1.2130   0.08694   0.07922  -0.0355   0.1111   1.0000
  15.250   1.2096   0.09105   0.08358  -0.0361   0.1037   1.0000
  15.500   1.2109   0.09416   0.08661  -0.0365   0.0969   1.0000
  15.750   1.2038   0.09913   0.09193  -0.0379   0.0910   1.0000
  16.000   1.2054   0.10232   0.09510  -0.0385   0.0852   1.0000
  16.250   1.1974   0.10764   0.10072  -0.0402   0.0809   1.0000
  16.500   1.1911   0.11263   0.10591  -0.0421   0.0766   1.0000
  16.750   1.1946   0.11563   0.10886  -0.0429   0.0722   1.0000
  17.000   1.1796   0.12275   0.11634  -0.0462   0.0699   1.0000
  17.250   1.1641   0.13021   0.12408  -0.0501   0.0679   1.0000
  17.500   1.1477   0.13819   0.13228  -0.0545   0.0663   1.0000
  17.750   1.1235   0.14856   0.14285  -0.0607   0.0657   1.0000
  18.000   1.0723   0.16812   0.16244  -0.0727   0.0678   1.0000
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