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EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E662 AIRFOIL (e662-il)
Reynolds number: 100,000
Max Cl/Cd: 46.55 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e662-il-100000.txt
Download as CSV file: xf-e662-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E662 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.5374   0.10957   0.10577  -0.0247   1.0000   0.1136
  -7.250  -0.5729   0.10660   0.10288  -0.0247   1.0000   0.1140
  -7.000  -0.6121   0.10240   0.09860  -0.0282   1.0000   0.1148
  -6.750  -0.6296   0.09723   0.09338  -0.0292   1.0000   0.1160
  -6.500  -0.6047   0.09514   0.09147  -0.0234   1.0000   0.1190
  -6.250  -0.6063   0.09234   0.08865  -0.0221   1.0000   0.1220
  -6.000  -0.6405   0.08773   0.08340  -0.0301   1.0000   0.1305
  -5.750  -0.6287   0.08264   0.07866  -0.0268   1.0000   0.1325
  -5.500  -0.6200   0.08055   0.07667  -0.0239   1.0000   0.1366
  -5.250  -0.6208   0.07584   0.07167  -0.0269   1.0000   0.1479
  -5.000  -0.6115   0.07363   0.06955  -0.0247   1.0000   0.1528
  -4.750  -0.6042   0.06988   0.06564  -0.0259   1.0000   0.1654
  -4.500  -0.5930   0.06667   0.06223  -0.0271   1.0000   0.1793
  -4.250  -0.5799   0.06391   0.05931  -0.0278   1.0000   0.1944
  -4.000  -0.5189   0.04766   0.04097  -0.0355   1.0000   0.0827
  -3.750  -0.4883   0.04372   0.03599  -0.0358   1.0000   0.0720
  -3.500  -0.4617   0.04204   0.03383  -0.0363   0.9993   0.0728
  -3.250  -0.4290   0.04052   0.03189  -0.0379   0.9966   0.0727
  -3.000  -0.3950   0.03921   0.03024  -0.0395   0.9942   0.0725
  -2.750  -0.3674   0.03785   0.02866  -0.0400   0.9916   0.0732
  -2.500  -0.3362   0.03699   0.02775  -0.0411   0.9878   0.0753
  -2.250  -0.3018   0.03721   0.02791  -0.0429   0.9845   0.0804
  -2.000  -0.2760   0.03701   0.02756  -0.0431   0.9801   0.0859
  -1.750  -0.2440   0.03671   0.02744  -0.0445   0.9751   0.0935
  -1.500  -0.2065   0.03724   0.02805  -0.0469   0.9720   0.1111
  -1.250  -0.1823   0.03596   0.02741  -0.0472   0.9662   0.1934
  -1.000  -0.1793   0.03534   0.02954  -0.0404   0.9617   0.7881
  -0.750  -0.1796   0.03619   0.03036  -0.0332   0.9525   0.8498
  -0.500  -0.1822   0.03727   0.03142  -0.0247   0.9454   0.9023
  -0.250   0.0140   0.04029   0.03376  -0.0514   0.9007   1.0000
   0.000   0.0385   0.03997   0.03325  -0.0513   0.8797   1.0000
   0.250  -0.0111   0.04125   0.03464  -0.0416   0.9166   1.0000
   0.500   0.0145   0.04149   0.03473  -0.0421   0.9009   1.0000
   0.750   0.1156   0.04053   0.03336  -0.0520   0.8437   1.0000
   1.000   0.1287   0.04062   0.03335  -0.0502   0.8321   1.0000
   1.250   0.1756   0.04118   0.03376  -0.0536   0.8254   1.0000
   1.500   0.1729   0.04101   0.03355  -0.0494   0.8131   1.0000
   1.750   0.1843   0.04112   0.03359  -0.0473   0.8022   1.0000
   2.000   0.2221   0.04146   0.03381  -0.0492   0.7957   1.0000
   2.250   0.2289   0.04157   0.03388  -0.0466   0.7840   1.0000
   2.500   0.2761   0.04196   0.03417  -0.0498   0.7794   1.0000
   2.750   0.2839   0.04214   0.03432  -0.0477   0.7671   1.0000
   3.000   0.3031   0.04253   0.03468  -0.0472   0.7571   1.0000
   3.250   0.3426   0.04274   0.03483  -0.0494   0.7512   1.0000
   3.500   0.3600   0.04317   0.03525  -0.0488   0.7403   1.0000
   3.750   0.4047   0.04323   0.03527  -0.0515   0.7358   1.0000
   4.000   0.4209   0.04370   0.03574  -0.0508   0.7243   1.0000
   4.250   0.4683   0.04358   0.03560  -0.0536   0.7208   1.0000
   4.500   0.4844   0.04405   0.03609  -0.0530   0.7090   1.0000
   4.750   0.5058   0.04450   0.03656  -0.0530   0.6986   1.0000
   5.000   0.5496   0.04416   0.03623  -0.0552   0.6940   1.0000
   5.250   0.5690   0.04465   0.03677  -0.0549   0.6827   1.0000
   5.500   0.6159   0.04399   0.03614  -0.0572   0.6791   1.0000
   5.750   0.6345   0.04448   0.03667  -0.0568   0.6672   1.0000
   6.000   0.6838   0.04344   0.03572  -0.0592   0.6643   1.0000
   6.250   0.7024   0.04388   0.03621  -0.0587   0.6519   1.0000
   6.500   0.7526   0.04254   0.03495  -0.0608   0.6494   1.0000
   6.750   0.7716   0.04289   0.03537  -0.0603   0.6368   1.0000
   7.000   0.7945   0.04304   0.03562  -0.0600   0.6252   1.0000
   7.250   0.8442   0.04125   0.03395  -0.0618   0.6220   1.0000
   7.500   0.8974   0.03898   0.03183  -0.0636   0.6200   1.0000
   7.750   0.9198   0.03884   0.03178  -0.0630   0.6075   1.0000
   8.000   0.9649   0.03683   0.02991  -0.0639   0.6024   1.0000
   8.250   1.0048   0.03520   0.02843  -0.0645   0.5937   1.0000
   8.500   1.0747   0.03143   0.02483  -0.0676   0.5908   1.0000
   8.750   1.1160   0.02991   0.02345  -0.0684   0.5771   1.0000
   9.000   1.1678   0.02796   0.02159  -0.0703   0.5612   1.0000
   9.250   1.1966   0.02755   0.02122  -0.0700   0.5391   1.0000
   9.500   1.2387   0.02661   0.02025  -0.0712   0.5142   1.0000
   9.750   1.2535   0.02713   0.02076  -0.0695   0.4874   1.0000
  10.000   1.2693   0.02768   0.02126  -0.0680   0.4601   1.0000
  10.250   1.2829   0.02840   0.02190  -0.0663   0.4325   1.0000
  10.500   1.2936   0.02931   0.02272  -0.0643   0.4051   1.0000
  10.750   1.3007   0.03044   0.02376  -0.0621   0.3783   1.0000
  11.000   1.3039   0.03184   0.02510  -0.0596   0.3520   1.0000
  11.250   1.3079   0.03328   0.02645  -0.0573   0.3264   1.0000
  11.500   1.3120   0.03480   0.02782  -0.0551   0.3019   1.0000
  11.750   1.3125   0.03658   0.02958  -0.0528   0.2779   1.0000
  12.000   1.3152   0.03835   0.03119  -0.0508   0.2555   1.0000
  12.250   1.3158   0.04032   0.03315  -0.0488   0.2337   1.0000
  12.500   1.3182   0.04229   0.03501  -0.0470   0.2140   1.0000
  12.750   1.3205   0.04438   0.03704  -0.0453   0.1951   1.0000
  13.000   1.3227   0.04656   0.03921  -0.0438   0.1777   1.0000
  13.250   1.3254   0.04878   0.04139  -0.0423   0.1619   1.0000
  13.500   1.3290   0.05104   0.04363  -0.0411   0.1475   1.0000
  13.750   1.3323   0.05339   0.04598  -0.0399   0.1344   1.0000
  14.000   1.3343   0.05586   0.04845  -0.0388   0.1226   1.0000
  14.250   1.3346   0.05846   0.05103  -0.0379   0.1117   1.0000
  14.500   1.3343   0.06115   0.05364  -0.0371   0.1014   1.0000
  14.750   1.3289   0.06441   0.05716  -0.0363   0.0927   1.0000
  15.000   1.3275   0.06752   0.06033  -0.0358   0.0841   1.0000
  15.250   1.3286   0.07046   0.06317  -0.0354   0.0756   1.0000
  15.500   1.3232   0.07418   0.06714  -0.0351   0.0687   1.0000
  15.750   1.3242   0.07750   0.07051  -0.0347   0.0616   1.0000
  16.000   1.3253   0.08074   0.07379  -0.0346   0.0559   1.0000
  16.250   1.3281   0.08420   0.07740  -0.0343   0.0512   1.0000
  16.500   1.3255   0.08799   0.08139  -0.0346   0.0478   1.0000
  16.750   1.3367   0.09051   0.08379  -0.0344   0.0439   1.0000
  17.000   1.3282   0.09523   0.08889  -0.0351   0.0425   1.0000
  17.250   1.3213   0.10001   0.09398  -0.0359   0.0413   1.0000
  17.500   1.3130   0.10504   0.09929  -0.0371   0.0404   1.0000
  17.750   1.3029   0.11040   0.10494  -0.0388   0.0396   1.0000
  18.000   1.2904   0.11623   0.11103  -0.0410   0.0392   1.0000
  18.250   1.2738   0.12292   0.11798  -0.0440   0.0390   1.0000
  18.500   1.2508   0.13099   0.12632  -0.0483   0.0392   1.0000
  18.750   1.2203   0.14103   0.13667  -0.0544   0.0398   1.0000
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