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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 200,000
Max Cl/Cd: 81.06 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e668-il-200000.txt
Download as CSV file: xf-e668-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 668 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1438   0.09363   0.08999  -0.1104   0.9578   0.0483
 -10.000  -0.1511   0.08977   0.08617  -0.1130   0.9529   0.0510
  -9.750  -0.1752   0.07914   0.07557  -0.1296   0.9477   0.0523
  -9.500  -0.1574   0.07696   0.07342  -0.1268   0.9469   0.0531
  -9.250  -0.1392   0.07521   0.07167  -0.1263   0.9459   0.0543
  -9.000  -0.1273   0.07162   0.06807  -0.1295   0.9444   0.0560
  -8.750  -0.1411   0.06849   0.06497  -0.1302   0.9384   0.0566
  -8.500  -0.1593   0.06319   0.05966  -0.1351   0.9326   0.0578
  -8.250  -0.1742   0.05885   0.05521  -0.1387   0.9287   0.0585
  -8.000  -0.2154   0.06003   0.05644  -0.1284   0.9191   0.0572
  -7.750  -0.2248   0.05661   0.05285  -0.1290   0.9155   0.0588
  -7.500  -0.2660   0.05770   0.05398  -0.1181   0.9068   0.0585
  -7.250  -0.3293   0.04225   0.03724  -0.1121   0.8995   0.0267
  -7.000  -0.3115   0.03705   0.03135  -0.1127   0.8980   0.0237
  -6.750  -0.3458   0.03784   0.03216  -0.1021   0.8898   0.0238
  -6.500  -0.3305   0.03428   0.02801  -0.1011   0.8869   0.0227
  -6.250  -0.3053   0.03180   0.02504  -0.1012   0.8851   0.0230
  -6.000  -0.2752   0.02994   0.02281  -0.1020   0.8838   0.0238
  -5.750  -0.2412   0.02853   0.02110  -0.1035   0.8826   0.0267
  -5.500  -0.2499   0.02875   0.02135  -0.0976   0.8762   0.0282
  -5.250  -0.2289   0.02792   0.02031  -0.0965   0.8729   0.0299
  -5.000  -0.2005   0.02663   0.01898  -0.0968   0.8706   0.0329
  -4.750  -0.1688   0.02575   0.01806  -0.0978   0.8689   0.0388
  -4.500  -0.1339   0.02490   0.01724  -0.0994   0.8675   0.0481
  -4.250  -0.0966   0.02407   0.01643  -0.1014   0.8664   0.0639
  -4.000  -0.1066   0.02447   0.01686  -0.0953   0.8583   0.0703
  -3.750  -0.0777   0.02383   0.01631  -0.0959   0.8554   0.0984
  -3.500  -0.0438   0.02294   0.01582  -0.0977   0.8534   0.1697
  -3.250  -0.0072   0.02212   0.01553  -0.1002   0.8519   0.2954
  -3.000   0.0306   0.02132   0.01536  -0.1027   0.8508   0.4551
  -2.750   0.0255   0.02165   0.01604  -0.0974   0.8421   0.5352
  -2.500   0.0489   0.02149   0.01639  -0.0960   0.8389   0.6694
  -2.250   0.0786   0.02168   0.01668  -0.0953   0.8367   0.7422
  -2.000   0.1127   0.02191   0.01683  -0.0955   0.8352   0.7809
  -1.750   0.1056   0.02269   0.01762  -0.0894   0.8252   0.8002
  -1.500   0.1327   0.02289   0.01774  -0.0884   0.8223   0.8235
  -1.250   0.1631   0.02294   0.01772  -0.0878   0.8205   0.8425
  -1.000   0.1597   0.02355   0.01832  -0.0822   0.8110   0.8578
  -0.750   0.1813   0.02355   0.01827  -0.0802   0.8074   0.8739
  -0.500   0.2075   0.02341   0.01808  -0.0787   0.8053   0.8899
  -0.250   0.2045   0.02381   0.01847  -0.0732   0.7958   0.9051
   0.000   0.2245   0.02363   0.01826  -0.0709   0.7920   0.9204
   0.250   0.2523   0.02331   0.01788  -0.0700   0.7899   0.9349
   0.500   0.2848   0.02299   0.01751  -0.0700   0.7885   0.9492
   0.750   0.2933   0.02349   0.01801  -0.0676   0.7774   0.9658
   1.000   0.3452   0.02334   0.01780  -0.0719   0.7759   0.9758
   1.250   0.4007   0.02314   0.01755  -0.0770   0.7748   0.9837
   1.500   0.4601   0.02287   0.01723  -0.0829   0.7742   0.9884
   1.750   0.5181   0.02247   0.01680  -0.0884   0.7737   0.9917
   2.000   0.5750   0.02202   0.01632  -0.0936   0.7733   0.9941
   2.250   0.6303   0.02148   0.01577  -0.0986   0.7727   0.9957
   2.500   0.5671   0.02247   0.01677  -0.0838   0.7524   1.0000
   2.750   0.6314   0.02152   0.01582  -0.0895   0.7552   1.0000
   3.000   0.6956   0.02072   0.01502  -0.0957   0.7564   1.0000
   3.250   0.6821   0.02085   0.01515  -0.0887   0.7447   1.0000
   3.500   0.7107   0.02054   0.01487  -0.0889   0.7397   1.0000
   3.750   0.7741   0.01941   0.01377  -0.0945   0.7419   1.0000
   4.000   0.7803   0.01952   0.01390  -0.0911   0.7309   1.0000
   4.250   0.8286   0.01863   0.01304  -0.0942   0.7296   1.0000
   4.500   0.8776   0.01768   0.01215  -0.0975   0.7282   1.0000
   4.750   0.8879   0.01769   0.01221  -0.0947   0.7168   1.0000
   5.000   0.9375   0.01669   0.01126  -0.0980   0.7144   1.0000
   5.250   0.9531   0.01658   0.01121  -0.0959   0.7034   1.0000
   5.500   1.0033   0.01558   0.01025  -0.0994   0.6992   1.0000
   5.750   1.0220   0.01540   0.01014  -0.0977   0.6868   1.0000
   6.000   1.0481   0.01509   0.00988  -0.0973   0.6741   1.0000
   6.250   1.0780   0.01475   0.00957  -0.0975   0.6598   1.0000
   6.500   1.1097   0.01444   0.00928  -0.0980   0.6428   1.0000
   6.750   1.1399   0.01427   0.00907  -0.0983   0.6223   1.0000
   7.000   1.1619   0.01438   0.00913  -0.0973   0.5979   1.0000
   7.250   1.1835   0.01460   0.00927  -0.0963   0.5710   1.0000
   7.500   1.2015   0.01499   0.00954  -0.0947   0.5425   1.0000
   7.750   1.2157   0.01553   0.00995  -0.0926   0.5136   1.0000
   8.000   1.2266   0.01620   0.01051  -0.0901   0.4848   1.0000
   8.250   1.2351   0.01697   0.01118  -0.0874   0.4561   1.0000
   8.500   1.2424   0.01784   0.01194  -0.0846   0.4278   1.0000
   8.750   1.2487   0.01880   0.01279  -0.0818   0.4000   1.0000
   9.000   1.2540   0.01987   0.01374  -0.0789   0.3723   1.0000
   9.250   1.2592   0.02101   0.01478  -0.0763   0.3449   1.0000
   9.500   1.2645   0.02220   0.01588  -0.0737   0.3175   1.0000
   9.750   1.2695   0.02348   0.01706  -0.0713   0.2912   1.0000
  10.000   1.2735   0.02488   0.01833  -0.0689   0.2658   1.0000
  10.250   1.2794   0.02623   0.01961  -0.0668   0.2404   1.0000
  10.500   1.2840   0.02771   0.02099  -0.0646   0.2167   1.0000
  10.750   1.2888   0.02924   0.02245  -0.0626   0.1939   1.0000
  11.000   1.2933   0.03086   0.02398  -0.0607   0.1728   1.0000
  11.250   1.2984   0.03249   0.02555  -0.0589   0.1529   1.0000
  11.500   1.3023   0.03428   0.02726  -0.0571   0.1354   1.0000
  11.750   1.3059   0.03615   0.02906  -0.0554   0.1203   1.0000
  12.000   1.3094   0.03810   0.03097  -0.0537   0.1068   1.0000
  12.250   1.3138   0.04004   0.03291  -0.0523   0.0949   1.0000
  12.500   1.3180   0.04207   0.03497  -0.0509   0.0845   1.0000
  12.750   1.3211   0.04427   0.03719  -0.0496   0.0759   1.0000
  13.000   1.3215   0.04678   0.03965  -0.0482   0.0689   1.0000
  13.250   1.3272   0.04888   0.04186  -0.0473   0.0624   1.0000
  13.500   1.3285   0.05146   0.04446  -0.0461   0.0573   1.0000
  13.750   1.3331   0.05377   0.04686  -0.0454   0.0525   1.0000
  14.000   1.3347   0.05647   0.04957  -0.0445   0.0487   1.0000
  14.250   1.3398   0.05887   0.05210  -0.0439   0.0450   1.0000
  14.500   1.3420   0.06158   0.05478  -0.0433   0.0420   1.0000
  14.750   1.3464   0.06420   0.05757  -0.0428   0.0391   1.0000
  15.000   1.3498   0.06691   0.06037  -0.0426   0.0366   1.0000
  15.250   1.3535   0.06966   0.06310  -0.0422   0.0341   1.0000
  15.500   1.3553   0.07273   0.06639  -0.0422   0.0320   1.0000
  15.750   1.3571   0.07577   0.06951  -0.0424   0.0300   1.0000
  16.000   1.3602   0.07874   0.07251  -0.0423   0.0281   1.0000
  16.250   1.3593   0.08238   0.07639  -0.0427   0.0264   1.0000
  16.500   1.3596   0.08581   0.07992  -0.0432   0.0249   1.0000
  16.750   1.3632   0.08877   0.08285  -0.0433   0.0233   1.0000
  17.000   1.3566   0.09344   0.08781  -0.0445   0.0221   1.0000
  17.250   1.3523   0.09777   0.09231  -0.0459   0.0208   1.0000
  17.500   1.3526   0.10130   0.09585  -0.0470   0.0197   1.0000
  17.750   1.3491   0.10565   0.10036  -0.0481   0.0188   1.0000
  18.000   1.3395   0.11120   0.10619  -0.0503   0.0180   1.0000
  18.250   1.3321   0.11640   0.11159  -0.0527   0.0172   1.0000
  18.500   1.3267   0.12128   0.11662  -0.0551   0.0165   1.0000
  18.750   1.3319   0.12388   0.11910  -0.0560   0.0155   1.0000
  19.000   1.3171   0.13086   0.12638  -0.0599   0.0153   1.0000
  19.250   1.3022   0.13808   0.13388  -0.0641   0.0150   1.0000
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