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EPPLER 328 AIRFOIL (e328-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 328 AIRFOIL (e328-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.1 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e328-il-1000000.txt
Download as CSV file: xf-e328-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 328 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3964   0.08359   0.08206  -0.0309   1.0000   0.0082
  -9.000  -0.4043   0.07839   0.07688  -0.0347   1.0000   0.0082
  -8.750  -0.4215   0.07269   0.07119  -0.0389   1.0000   0.0083
  -8.500  -0.4409   0.06876   0.06723  -0.0390   1.0000   0.0082
  -8.250  -0.4459   0.06392   0.06232  -0.0415   0.9835   0.0082
  -8.000  -0.4083   0.05569   0.05383  -0.0539   0.9307   0.0085
  -7.750  -0.3951   0.05108   0.04871  -0.0564   0.8387   0.0087
  -7.500  -0.3995   0.04747   0.04479  -0.0531   0.7975   0.0091
  -7.250  -0.3963   0.04488   0.04197  -0.0507   0.7685   0.0090
  -7.000  -0.3916   0.03854   0.03521  -0.0464   0.7493   0.0097
  -6.750  -0.3876   0.03488   0.03119  -0.0430   0.7301   0.0098
  -6.500  -0.3907   0.03052   0.02652  -0.0395   0.7135   0.0101
  -6.250  -0.3765   0.02899   0.02480  -0.0377   0.6954   0.0102
  -6.000  -0.3603   0.02775   0.02341  -0.0363   0.6792   0.0104
  -5.750  -0.3573   0.01906   0.01360  -0.0297   0.6700   0.0074
  -5.500  -0.3368   0.01676   0.01105  -0.0283   0.6558   0.0068
  -5.250  -0.3135   0.01510   0.00909  -0.0272   0.6424   0.0066
  -5.000  -0.2890   0.01396   0.00774  -0.0263   0.6292   0.0066
  -4.750  -0.2644   0.01317   0.00678  -0.0255   0.6166   0.0069
  -4.500  -0.2393   0.01270   0.00616  -0.0248   0.6039   0.0074
  -4.250  -0.2169   0.01192   0.00528  -0.0237   0.5918   0.0077
  -4.000  -0.1926   0.01156   0.00487  -0.0230   0.5802   0.0081
  -3.750  -0.1684   0.01120   0.00445  -0.0223   0.5696   0.0084
  -3.500  -0.1439   0.01092   0.00411  -0.0215   0.5590   0.0088
  -3.250  -0.1195   0.01063   0.00375  -0.0208   0.5482   0.0090
  -3.000  -0.0946   0.01039   0.00345  -0.0201   0.5382   0.0093
  -2.750  -0.0698   0.01017   0.00316  -0.0195   0.5287   0.0097
  -2.500  -0.0454   0.00988   0.00283  -0.0188   0.5196   0.0107
  -2.250  -0.0199   0.00971   0.00262  -0.0182   0.5108   0.0120
  -2.000   0.0053   0.00952   0.00238  -0.0176   0.5017   0.0141
  -1.750   0.0293   0.00920   0.00216  -0.0168   0.4937   0.0408
  -1.500   0.0539   0.00898   0.00205  -0.0162   0.4856   0.0809
  -1.000   0.0833   0.00695   0.00160  -0.0120   0.4721   0.5647
  -0.750   0.0963   0.00628   0.00171  -0.0089   0.4656   0.8046
  -0.500   0.1223   0.00644   0.00188  -0.0081   0.4584   0.8309
  -0.250   0.1489   0.00660   0.00197  -0.0076   0.4513   0.8419
   0.000   0.1762   0.00673   0.00209  -0.0072   0.4452   0.8502
   0.250   0.2022   0.00690   0.00223  -0.0066   0.4384   0.8598
   0.500   0.2291   0.00706   0.00236  -0.0061   0.4325   0.8663
   0.750   0.2561   0.00719   0.00245  -0.0058   0.4266   0.8722
   1.000   0.2825   0.00729   0.00250  -0.0053   0.4204   0.8759
   1.250   0.3108   0.00731   0.00250  -0.0054   0.4153   0.8771
   1.500   0.3388   0.00736   0.00249  -0.0055   0.4096   0.8782
   1.750   0.3666   0.00743   0.00250  -0.0056   0.4042   0.8792
   2.000   0.3950   0.00745   0.00251  -0.0058   0.3996   0.8804
   2.250   0.4229   0.00751   0.00253  -0.0059   0.3943   0.8816
   2.500   0.4506   0.00760   0.00256  -0.0060   0.3892   0.8827
   2.750   0.4791   0.00762   0.00258  -0.0062   0.3850   0.8837
   3.000   0.5072   0.00768   0.00261  -0.0064   0.3803   0.8847
   3.250   0.5347   0.00778   0.00266  -0.0064   0.3754   0.8857
   3.500   0.5629   0.00784   0.00271  -0.0066   0.3714   0.8867
   3.750   0.5910   0.00788   0.00275  -0.0068   0.3669   0.8877
   4.000   0.6183   0.00794   0.00278  -0.0068   0.3623   0.8888
   4.250   0.6455   0.00802   0.00285  -0.0069   0.3577   0.8899
   4.500   0.6734   0.00807   0.00290  -0.0070   0.3538   0.8909
   4.750   0.7008   0.00814   0.00298  -0.0070   0.3493   0.8920
   5.000   0.7275   0.00827   0.00308  -0.0070   0.3443   0.8931
   5.250   0.7553   0.00833   0.00316  -0.0071   0.3406   0.8943
   5.500   0.7827   0.00841   0.00325  -0.0072   0.3359   0.8956
   5.750   0.8093   0.00853   0.00336  -0.0072   0.3307   0.8970
   6.000   0.8365   0.00863   0.00347  -0.0072   0.3262   0.8985
   6.250   0.8639   0.00871   0.00357  -0.0073   0.3214   0.8998
   6.500   0.8905   0.00885   0.00369  -0.0073   0.3161   0.9010
   6.750   0.9175   0.00896   0.00381  -0.0074   0.3112   0.9022
   7.000   0.9445   0.00905   0.00393  -0.0075   0.3057   0.9035
   7.250   0.9699   0.00920   0.00406  -0.0073   0.2994   0.9051
   7.500   0.9965   0.00929   0.00419  -0.0072   0.2940   0.9066
   7.750   1.0220   0.00944   0.00435  -0.0071   0.2872   0.9082
   8.000   1.0478   0.00958   0.00451  -0.0069   0.2810   0.9099
   8.250   1.0732   0.00974   0.00468  -0.0067   0.2739   0.9117
   8.500   1.0982   0.00992   0.00488  -0.0065   0.2664   0.9137
   8.750   1.1228   0.01013   0.00508  -0.0062   0.2579   0.9158
   9.000   1.1477   0.01033   0.00529  -0.0060   0.2497   0.9177
   9.250   1.1708   0.01058   0.00553  -0.0054   0.2397   0.9201
   9.500   1.1931   0.01084   0.00579  -0.0048   0.2288   0.9225
   9.750   1.2152   0.01112   0.00606  -0.0041   0.2174   0.9252
  10.000   1.2366   0.01145   0.00637  -0.0033   0.2056   0.9282
  10.250   1.2564   0.01186   0.00674  -0.0023   0.1910   0.9314
  10.500   1.2749   0.01227   0.00713  -0.0011   0.1771   0.9350
  10.750   1.2915   0.01271   0.00754   0.0005   0.1638   0.9395
  11.000   1.3071   0.01318   0.00799   0.0022   0.1509   0.9448
  11.250   1.3192   0.01371   0.00849   0.0045   0.1366   0.9517
  11.500   1.3259   0.01428   0.00902   0.0079   0.1224   0.9637
  11.750   1.3430   0.01493   0.00966   0.0088   0.1103   0.9784
  12.000   1.3634   0.01586   0.01052   0.0085   0.0939   1.0000
  12.250   1.3735   0.01659   0.01122   0.0105   0.0855   1.0000
  12.500   1.3822   0.01738   0.01200   0.0126   0.0772   1.0000
  12.750   1.3863   0.01841   0.01300   0.0150   0.0675   1.0000
  13.000   1.3915   0.01946   0.01405   0.0171   0.0617   1.0000
  13.250   1.3926   0.02083   0.01541   0.0192   0.0545   1.0000
  13.500   1.3984   0.02206   0.01668   0.0206   0.0510   1.0000
  13.750   1.3975   0.02388   0.01850   0.0221   0.0454   1.0000
  14.000   1.4014   0.02554   0.02021   0.0229   0.0424   1.0000
  14.250   1.3985   0.02786   0.02256   0.0237   0.0379   1.0000
  14.500   1.4007   0.02993   0.02470   0.0241   0.0363   1.0000
  14.750   1.3985   0.03249   0.02730   0.0243   0.0327   1.0000
  15.000   1.3935   0.03545   0.03031   0.0244   0.0302   1.0000
  15.250   1.3904   0.03830   0.03322   0.0242   0.0276   1.0000
  15.500   1.3860   0.04137   0.03636   0.0240   0.0263   1.0000
  15.750   1.3777   0.04493   0.03998   0.0235   0.0244   1.0000
  16.000   1.3725   0.04822   0.04335   0.0230   0.0230   1.0000
  16.250   1.3669   0.05164   0.04685   0.0223   0.0222   1.0000
  16.500   1.3576   0.05561   0.05089   0.0214   0.0208   1.0000
  16.750   1.3477   0.05980   0.05514   0.0203   0.0195   1.0000
  17.000   1.3420   0.06355   0.05898   0.0192   0.0185   1.0000
  17.250   1.3343   0.06765   0.06314   0.0179   0.0173   1.0000
  17.500   1.3255   0.07196   0.06751   0.0165   0.0164   1.0000
  17.750   1.3169   0.07638   0.07201   0.0150   0.0158   1.0000
  18.000   1.3101   0.08062   0.07633   0.0134   0.0151   1.0000
  18.250   1.3040   0.08482   0.08062   0.0117   0.0144   1.0000
  18.500   1.2969   0.08926   0.08513   0.0100   0.0139   1.0000
  18.750   1.2867   0.09423   0.09016   0.0079   0.0126   1.0000
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