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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 200,000
Max Cl/Cd: 82.19 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e68-il-200000.txt
Download as CSV file: xf-e68-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4338   0.09856   0.09537  -0.0398   1.0000   0.0645
  -9.250  -0.4451   0.09602   0.09289  -0.0386   1.0000   0.0652
  -9.000  -0.5775   0.06158   0.05825  -0.0669   0.9905   0.0372
  -8.750  -0.5845   0.05349   0.04982  -0.0742   0.9828   0.0354
  -8.500  -0.6074   0.04086   0.03572  -0.0789   0.9719   0.0307
  -8.250  -0.5929   0.03809   0.03256  -0.0788   0.9654   0.0305
  -8.000  -0.5703   0.03462   0.02864  -0.0803   0.9612   0.0305
  -7.750  -0.5437   0.03084   0.02452  -0.0825   0.9588   0.0316
  -7.500  -0.5246   0.02936   0.02291  -0.0819   0.9525   0.0328
  -7.250  -0.4952   0.02772   0.02105  -0.0830   0.9487   0.0340
  -7.000  -0.4614   0.02595   0.01900  -0.0847   0.9462   0.0350
  -6.750  -0.4327   0.02456   0.01742  -0.0852   0.9423   0.0364
  -6.500  -0.4079   0.02346   0.01616  -0.0849   0.9367   0.0378
  -6.250  -0.3760   0.02189   0.01451  -0.0862   0.9336   0.0406
  -6.000  -0.3392   0.02102   0.01362  -0.0883   0.9315   0.0465
  -5.750  -0.3185   0.02010   0.01269  -0.0874   0.9250   0.0539
  -5.500  -0.2879   0.01904   0.01166  -0.0883   0.9208   0.0747
  -5.250  -0.2514   0.01826   0.01097  -0.0905   0.9183   0.1033
  -5.000  -0.2123   0.01765   0.01046  -0.0931   0.9164   0.1340
  -4.750  -0.1945   0.01740   0.01029  -0.0916   0.9083   0.1618
  -4.500  -0.1587   0.01687   0.00989  -0.0935   0.9052   0.2031
  -4.250  -0.1201   0.01629   0.00946  -0.0959   0.9031   0.2482
  -4.000  -0.0797   0.01574   0.00906  -0.0987   0.9016   0.2996
  -3.750  -0.0636   0.01561   0.00903  -0.0966   0.8927   0.3378
  -3.500  -0.0259   0.01517   0.00876  -0.0987   0.8902   0.3923
  -3.250   0.0146   0.01476   0.00847  -0.1012   0.8885   0.4465
  -3.000   0.0548   0.01439   0.00822  -0.1035   0.8869   0.4955
  -2.750   0.0719   0.01440   0.00830  -0.1014   0.8779   0.5292
  -2.500   0.1087   0.01411   0.00807  -0.1030   0.8751   0.5683
  -2.250   0.1472   0.01380   0.00783  -0.1048   0.8730   0.6052
  -2.000   0.1681   0.01381   0.00790  -0.1033   0.8652   0.6343
  -1.750   0.2016   0.01359   0.00773  -0.1040   0.8613   0.6654
  -1.500   0.2382   0.01334   0.00751  -0.1053   0.8587   0.6956
  -1.250   0.2603   0.01336   0.00758  -0.1039   0.8512   0.7215
  -1.000   0.2916   0.01319   0.00744  -0.1042   0.8465   0.7485
  -0.750   0.3265   0.01296   0.00724  -0.1050   0.8434   0.7726
  -0.500   0.3455   0.01303   0.00735  -0.1029   0.8349   0.7960
  -0.250   0.3762   0.01284   0.00718  -0.1029   0.8304   0.8182
   0.000   0.4008   0.01279   0.00715  -0.1018   0.8243   0.8410
   0.250   0.4236   0.01272   0.00711  -0.1001   0.8174   0.8621
   0.500   0.4544   0.01252   0.00688  -0.1000   0.8134   0.8842
   0.750   0.4690   0.01254   0.00695  -0.0968   0.8041   0.9069
   1.000   0.5003   0.01233   0.00672  -0.0969   0.7995   0.9290
   1.250   0.5301   0.01231   0.00672  -0.0970   0.7911   0.9498
   1.500   0.5772   0.01215   0.00651  -0.1007   0.7858   0.9651
   1.750   0.6241   0.01209   0.00645  -0.1046   0.7782   0.9787
   2.000   0.6766   0.01194   0.00626  -0.1097   0.7713   0.9882
   2.250   0.7253   0.01187   0.00619  -0.1142   0.7625   1.0000
   2.500   0.7482   0.01177   0.00603  -0.1134   0.7547   1.0000
   2.750   0.7579   0.01184   0.00610  -0.1102   0.7438   1.0000
   3.000   0.7783   0.01188   0.00610  -0.1088   0.7342   1.0000
   3.250   0.8065   0.01185   0.00602  -0.1089   0.7254   1.0000
   3.500   0.8276   0.01193   0.00611  -0.1076   0.7139   1.0000
   3.750   0.8520   0.01200   0.00616  -0.1069   0.7029   1.0000
   4.000   0.8787   0.01205   0.00618  -0.1066   0.6923   1.0000
   4.250   0.9057   0.01210   0.00620  -0.1064   0.6811   1.0000
   4.500   0.9288   0.01220   0.00632  -0.1054   0.6682   1.0000
   4.750   0.9526   0.01230   0.00643  -0.1045   0.6548   1.0000
   5.000   0.9763   0.01241   0.00654  -0.1037   0.6410   1.0000
   5.250   0.9998   0.01254   0.00667  -0.1027   0.6265   1.0000
   5.500   1.0228   0.01268   0.00681  -0.1017   0.6112   1.0000
   5.750   1.0453   0.01283   0.00695  -0.1006   0.5948   1.0000
   6.000   1.0675   0.01302   0.00710  -0.0994   0.5778   1.0000
   6.250   1.0874   0.01323   0.00734  -0.0978   0.5590   1.0000
   6.500   1.1067   0.01347   0.00757  -0.0962   0.5388   1.0000
   6.750   1.1256   0.01375   0.00780  -0.0944   0.5180   1.0000
   7.000   1.1418   0.01406   0.00809  -0.0922   0.4941   1.0000
   7.250   1.1570   0.01442   0.00841  -0.0898   0.4691   1.0000
   7.500   1.1704   0.01486   0.00878  -0.0872   0.4426   1.0000
   7.750   1.1811   0.01534   0.00918  -0.0841   0.4149   1.0000
   8.000   1.1897   0.01588   0.00964  -0.0807   0.3864   1.0000
   8.250   1.1970   0.01654   0.01019  -0.0772   0.3564   1.0000
   8.500   1.2028   0.01731   0.01083  -0.0736   0.3240   1.0000
   8.750   1.2072   0.01822   0.01158  -0.0700   0.2896   1.0000
   9.000   1.2103   0.01927   0.01245  -0.0664   0.2555   1.0000
   9.250   1.2136   0.02041   0.01343  -0.0631   0.2232   1.0000
   9.500   1.2180   0.02159   0.01447  -0.0602   0.1934   1.0000
   9.750   1.2230   0.02283   0.01559  -0.0574   0.1682   1.0000
  10.000   1.2291   0.02408   0.01675  -0.0550   0.1452   1.0000
  10.250   1.2333   0.02550   0.01807  -0.0525   0.1254   1.0000
  10.500   1.2391   0.02689   0.01941  -0.0503   0.1063   1.0000
  10.750   1.2423   0.02853   0.02096  -0.0479   0.0889   1.0000
  11.000   1.2437   0.03037   0.02272  -0.0456   0.0740   1.0000
  11.250   1.2445   0.03236   0.02471  -0.0433   0.0599   1.0000
  11.500   1.2417   0.03473   0.02705  -0.0410   0.0499   1.0000
  11.750   1.2418   0.03696   0.02930  -0.0390   0.0435   1.0000
  12.000   1.2408   0.03938   0.03179  -0.0372   0.0393   1.0000
  12.250   1.2445   0.04145   0.03394  -0.0358   0.0361   1.0000
  12.500   1.2444   0.04394   0.03644  -0.0344   0.0338   1.0000
  12.750   1.2464   0.04639   0.03896  -0.0331   0.0318   1.0000
  13.000   1.2525   0.04849   0.04119  -0.0321   0.0302   1.0000
  13.250   1.2585   0.05066   0.04347  -0.0311   0.0289   1.0000
  13.500   1.2645   0.05288   0.04575  -0.0303   0.0277   1.0000
  13.750   1.2714   0.05511   0.04806  -0.0295   0.0268   1.0000
  14.000   1.2839   0.05750   0.05046  -0.0283   0.0255   1.0000
  14.250   1.2904   0.05996   0.05311  -0.0277   0.0249   1.0000
  14.500   1.2941   0.06259   0.05594  -0.0272   0.0242   1.0000
  14.750   1.2968   0.06543   0.05897  -0.0269   0.0234   1.0000
  15.000   1.2988   0.06842   0.06215  -0.0267   0.0227   1.0000
  15.250   1.3000   0.07174   0.06567  -0.0265   0.0224   1.0000
  15.500   1.2987   0.07534   0.06947  -0.0266   0.0220   1.0000
  15.750   1.2951   0.07933   0.07366  -0.0269   0.0217   1.0000
  16.000   1.2889   0.08371   0.07825  -0.0276   0.0215   1.0000
  16.250   1.2804   0.08852   0.08329  -0.0287   0.0213   1.0000
  16.500   1.2694   0.09384   0.08883  -0.0303   0.0213   1.0000
  16.750   1.2560   0.09972   0.09495  -0.0324   0.0212   1.0000
  17.000   1.2397   0.10629   0.10176  -0.0352   0.0213   1.0000
  17.250   1.2168   0.11439   0.11015  -0.0393   0.0215   1.0000
  17.500   1.1907   0.12359   0.11963  -0.0446   0.0217   1.0000
  17.750   1.1611   0.13426   0.13057  -0.0513   0.0221   1.0000
  18.000   1.1261   0.14724   0.14381  -0.0600   0.0227   1.0000
  18.250   1.0817   0.16434   0.16112  -0.0717   0.0236   1.0000
  18.500   1.0387   0.18344   0.18028  -0.0835   0.0249   1.0000
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