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EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 100,000
Max Cl/Cd: 52.87 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e433-il-100000.txt
Download as CSV file: xf-e433-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4311   0.11129   0.10730  -0.0339   0.9938   0.0916
  -7.750  -0.4565   0.10792   0.10400  -0.0403   0.9879   0.0931
  -7.500  -0.4839   0.10419   0.10025  -0.0467   0.9824   0.0935
  -7.250  -0.4354   0.09988   0.09598  -0.0408   0.9812   0.0980
  -7.000  -0.4394   0.09710   0.09323  -0.0413   0.9766   0.1005
  -6.750  -0.4460   0.09287   0.08899  -0.0467   0.9720   0.1038
  -6.500  -0.4726   0.08898   0.08500  -0.0504   0.9658   0.1071
  -6.250  -0.4785   0.08381   0.07967  -0.0543   0.9612   0.1099
  -6.000  -0.4571   0.08094   0.07692  -0.0529   0.9577   0.1138
  -5.750  -0.4591   0.07793   0.07382  -0.0531   0.9530   0.1198
  -5.500  -0.4541   0.07348   0.06919  -0.0561   0.9487   0.1267
  -5.250  -0.4405   0.07016   0.06550  -0.0598   0.9440   0.1401
  -5.000  -0.4313   0.06713   0.06264  -0.0576   0.9400   0.1436
  -4.750  -0.4160   0.06397   0.05928  -0.0594   0.9356   0.1577
  -4.500  -0.3885   0.06084   0.05604  -0.0621   0.9317   0.1743
  -4.250  -0.3785   0.05844   0.05357  -0.0613   0.9267   0.1903
  -4.000  -0.3106   0.04543   0.03828  -0.0670   0.9241   0.0612
  -3.750  -0.2723   0.04198   0.03395  -0.0681   0.9202   0.0529
  -3.500  -0.2288   0.03980   0.03128  -0.0709   0.9167   0.0523
  -3.250  -0.2114   0.03878   0.02991  -0.0692   0.9108   0.0540
  -3.000  -0.1807   0.03701   0.02795  -0.0698   0.9063   0.0565
  -2.750  -0.1410   0.03583   0.02668  -0.0716   0.9025   0.0600
  -2.500  -0.1207   0.03527   0.02597  -0.0703   0.8966   0.0662
  -2.250  -0.0934   0.03435   0.02518  -0.0705   0.8915   0.0782
  -2.000  -0.0541   0.03314   0.02428  -0.0726   0.8877   0.1247
  -1.750  -0.0502   0.03067   0.02490  -0.0675   0.8829   0.7246
  -1.500  -0.0535   0.03155   0.02578  -0.0593   0.8761   0.8118
  -1.250  -0.0478   0.03222   0.02635  -0.0519   0.8713   0.8630
  -1.000  -0.0574   0.03228   0.02637  -0.0445   0.8630   0.8903
  -0.750  -0.0497   0.03232   0.02631  -0.0385   0.8575   0.9309
  -0.500   0.1619   0.03434   0.02762  -0.0710   0.8579   1.0000
  -0.250   0.1612   0.03450   0.02770  -0.0673   0.8491   1.0000
   0.000   0.1859   0.03460   0.02764  -0.0676   0.8430   1.0000
   0.250   0.1855   0.03476   0.02773  -0.0638   0.8338   1.0000
   0.500   0.2116   0.03483   0.02768  -0.0642   0.8276   1.0000
   0.750   0.2088   0.03498   0.02777  -0.0601   0.8178   1.0000
   1.000   0.2371   0.03506   0.02773  -0.0607   0.8121   1.0000
   1.250   0.2345   0.03521   0.02784  -0.0566   0.8016   1.0000
   1.500   0.2699   0.03531   0.02782  -0.0583   0.7965   1.0000
   1.750   0.2773   0.03567   0.02813  -0.0561   0.7859   1.0000
   2.000   0.3190   0.03576   0.02812  -0.0587   0.7811   1.0000
   2.250   0.3321   0.03626   0.02858  -0.0576   0.7704   1.0000
   2.500   0.3762   0.03628   0.02852  -0.0604   0.7659   1.0000
   2.750   0.3921   0.03684   0.02905  -0.0598   0.7548   1.0000
   3.000   0.4378   0.03673   0.02889  -0.0627   0.7508   1.0000
   3.250   0.4545   0.03734   0.02949  -0.0621   0.7393   1.0000
   3.500   0.5018   0.03705   0.02917  -0.0650   0.7356   1.0000
   3.750   0.5187   0.03769   0.02982  -0.0645   0.7238   1.0000
   4.000   0.5675   0.03718   0.02931  -0.0674   0.7205   1.0000
   4.250   0.5846   0.03782   0.02997  -0.0668   0.7083   1.0000
   4.500   0.6349   0.03704   0.02920  -0.0696   0.7054   1.0000
   4.750   0.6521   0.03767   0.02986  -0.0690   0.6930   1.0000
   5.000   0.7031   0.03663   0.02889  -0.0717   0.6904   1.0000
   5.250   0.7214   0.03715   0.02945  -0.0710   0.6777   1.0000
   5.500   0.7740   0.03572   0.02809  -0.0736   0.6755   1.0000
   5.750   0.7929   0.03613   0.02858  -0.0728   0.6628   1.0000
   6.000   0.8177   0.03620   0.02872  -0.0726   0.6519   1.0000
   6.250   0.8680   0.03445   0.02706  -0.0745   0.6486   1.0000
   6.500   0.9250   0.03212   0.02487  -0.0769   0.6469   1.0000
   6.750   0.9909   0.02945   0.02236  -0.0806   0.6453   1.0000
   7.000   1.0151   0.02917   0.02217  -0.0798   0.6324   1.0000
   7.500   1.1082   0.02628   0.01954  -0.0834   0.6119   1.0000
   7.750   1.1557   0.02496   0.01832  -0.0855   0.5978   1.0000
   8.000   1.1827   0.02459   0.01804  -0.0849   0.5795   1.0000
   8.250   1.2142   0.02411   0.01760  -0.0850   0.5596   1.0000
   8.500   1.2463   0.02374   0.01723  -0.0852   0.5374   1.0000
   8.750   1.2641   0.02394   0.01744  -0.0834   0.5133   1.0000
   9.000   1.2820   0.02425   0.01771  -0.0817   0.4881   1.0000
   9.250   1.3000   0.02464   0.01800  -0.0801   0.4621   1.0000
   9.500   1.3091   0.02538   0.01870  -0.0774   0.4363   1.0000
   9.750   1.3174   0.02623   0.01949  -0.0747   0.4107   1.0000
  10.000   1.3264   0.02714   0.02029  -0.0722   0.3857   1.0000
  10.250   1.3299   0.02827   0.02140  -0.0691   0.3612   1.0000
  10.500   1.3342   0.02948   0.02252  -0.0663   0.3375   1.0000
  10.750   1.3372   0.03080   0.02378  -0.0635   0.3145   1.0000
  11.000   1.3395   0.03225   0.02517  -0.0608   0.2922   1.0000
  11.250   1.3406   0.03383   0.02670  -0.0582   0.2707   1.0000
  11.500   1.3426   0.03548   0.02826  -0.0558   0.2501   1.0000
  11.750   1.3423   0.03732   0.03011  -0.0533   0.2300   1.0000
  12.000   1.3424   0.03924   0.03197  -0.0511   0.2112   1.0000
  12.250   1.3438   0.04123   0.03383  -0.0491   0.1934   1.0000
  12.500   1.3431   0.04341   0.03601  -0.0472   0.1763   1.0000
  12.750   1.3429   0.04567   0.03828  -0.0454   0.1605   1.0000
  13.000   1.3430   0.04803   0.04063  -0.0438   0.1459   1.0000
  13.250   1.3442   0.05043   0.04302  -0.0424   0.1325   1.0000
  13.500   1.3459   0.05290   0.04546  -0.0411   0.1203   1.0000
  13.750   1.3503   0.05530   0.04781  -0.0401   0.1090   1.0000
  14.000   1.3506   0.05797   0.05061  -0.0390   0.0997   1.0000
  14.250   1.3550   0.06065   0.05340  -0.0380   0.0910   1.0000
  14.500   1.3633   0.06309   0.05578  -0.0373   0.0829   1.0000
  14.750   1.3635   0.06603   0.05893  -0.0365   0.0768   1.0000
  15.000   1.3727   0.06870   0.06162  -0.0359   0.0705   1.0000
  15.250   1.3702   0.07199   0.06516  -0.0353   0.0661   1.0000
  15.500   1.3825   0.07466   0.06777  -0.0350   0.0607   1.0000
  15.750   1.3739   0.07868   0.07215  -0.0346   0.0580   1.0000
  16.000   1.3691   0.08242   0.07612  -0.0345   0.0550   1.0000
  16.250   1.3797   0.08552   0.07917  -0.0344   0.0509   1.0000
  16.500   1.3629   0.09058   0.08461  -0.0348   0.0497   1.0000
  16.750   1.3471   0.09589   0.09026  -0.0358   0.0484   1.0000
  17.000   1.3322   0.10138   0.09603  -0.0371   0.0472   1.0000
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