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EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 664 AIRFOIL (e664-il)
Reynolds number: 500,000
Max Cl/Cd: 90.82 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e664-il-500000.txt
Download as CSV file: xf-e664-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 664 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2786   0.07838   0.07572  -0.1227   0.9119   0.0285
 -12.250  -0.3010   0.07023   0.06729  -0.1304   0.8901   0.0284
 -12.000  -0.3271   0.06534   0.06218  -0.1326   0.8738   0.0285
 -11.750  -0.3513   0.06169   0.05832  -0.1326   0.8622   0.0285
  -9.750  -0.5066   0.03147   0.02584  -0.1039   0.8156   0.0193
  -9.500  -0.4866   0.02775   0.02203  -0.1039   0.8132   0.0182
  -9.250  -0.4732   0.02508   0.01904  -0.1022   0.8102   0.0174
  -9.000  -0.4533   0.02306   0.01673  -0.1013   0.8077   0.0171
  -8.750  -0.4304   0.02172   0.01520  -0.1009   0.8053   0.0172
  -8.500  -0.4032   0.02042   0.01373  -0.1012   0.8032   0.0172
  -8.250  -0.3739   0.01936   0.01255  -0.1018   0.8013   0.0173
  -8.000  -0.3474   0.01859   0.01168  -0.1019   0.7993   0.0178
  -7.750  -0.3218   0.01787   0.01089  -0.1018   0.7974   0.0181
  -7.500  -0.2987   0.01721   0.01019  -0.1013   0.7955   0.0184
  -7.250  -0.2774   0.01668   0.00961  -0.1005   0.7933   0.0188
  -7.000  -0.2570   0.01620   0.00908  -0.0994   0.7909   0.0194
  -6.750  -0.2405   0.01549   0.00836  -0.0979   0.7887   0.0200
  -6.500  -0.2239   0.01502   0.00788  -0.0963   0.7867   0.0209
  -6.250  -0.2068   0.01465   0.00748  -0.0947   0.7848   0.0216
  -6.000  -0.1882   0.01433   0.00710  -0.0934   0.7830   0.0224
  -5.750  -0.1683   0.01404   0.00677  -0.0922   0.7811   0.0233
  -5.500  -0.1502   0.01364   0.00638  -0.0908   0.7791   0.0250
  -5.250  -0.1296   0.01336   0.00610  -0.0898   0.7771   0.0272
  -5.000  -0.1094   0.01304   0.00581  -0.0887   0.7752   0.0335
  -4.750  -0.0938   0.01245   0.00548  -0.0869   0.7732   0.0769
  -4.500  -0.0755   0.01202   0.00526  -0.0856   0.7713   0.1268
  -4.250  -0.0568   0.01158   0.00505  -0.0845   0.7694   0.1840
  -4.000  -0.0397   0.01103   0.00483  -0.0832   0.7676   0.2703
  -3.750  -0.0262   0.01026   0.00457  -0.0815   0.7656   0.4035
  -3.500  -0.0183   0.00894   0.00430  -0.0789   0.7636   0.6371
  -3.250   0.0069   0.00930   0.00490  -0.0779   0.7617   0.7256
  -3.000   0.0349   0.00967   0.00525  -0.0777   0.7597   0.7449
  -2.750   0.0630   0.01011   0.00564  -0.0774   0.7577   0.7583
  -2.500   0.0913   0.01057   0.00606  -0.0771   0.7558   0.7678
  -2.250   0.1191   0.01109   0.00656  -0.0765   0.7539   0.7744
  -2.000   0.1475   0.01153   0.00697  -0.0762   0.7523   0.7792
  -1.750   0.1770   0.01167   0.00701  -0.0768   0.7506   0.7864
  -1.500   0.2031   0.01227   0.00763  -0.0756   0.7488   0.7896
  -1.250   0.2285   0.01291   0.00831  -0.0741   0.7468   0.7945
  -1.000   0.2539   0.01324   0.00862  -0.0735   0.7446   0.8035
  -0.750   0.2799   0.01372   0.00912  -0.0720   0.7425   0.8063
  -0.500   0.3069   0.01395   0.00934  -0.0715   0.7403   0.8096
  -0.250   0.3342   0.01391   0.00926  -0.0717   0.7380   0.8127
   0.000   0.3636   0.01369   0.00895  -0.0732   0.7355   0.8178
   0.250   0.3913   0.01366   0.00888  -0.0732   0.7329   0.8187
   0.500   0.4148   0.01358   0.00883  -0.0724   0.7299   0.8197
   0.750   0.4399   0.01353   0.00879  -0.0720   0.7268   0.8208
   1.000   0.4664   0.01345   0.00871  -0.0720   0.7238   0.8219
   1.250   0.4947   0.01335   0.00858  -0.0723   0.7211   0.8231
   1.500   0.5243   0.01328   0.00847  -0.0729   0.7185   0.8244
   1.750   0.5505   0.01322   0.00841  -0.0730   0.7153   0.8259
   2.000   0.5756   0.01309   0.00831  -0.0729   0.7115   0.8274
   2.250   0.6036   0.01296   0.00818  -0.0734   0.7079   0.8293
   2.500   0.6343   0.01281   0.00800  -0.0745   0.7047   0.8307
   2.750   0.6669   0.01271   0.00784  -0.0761   0.7014   0.8319
   3.000   0.6915   0.01256   0.00775  -0.0759   0.6969   0.8332
   3.250   0.7165   0.01240   0.00762  -0.0755   0.6923   0.8341
   3.500   0.7445   0.01226   0.00747  -0.0757   0.6883   0.8348
   3.750   0.7718   0.01216   0.00738  -0.0759   0.6841   0.8355
   4.000   0.7951   0.01204   0.00733  -0.0752   0.6783   0.8363
   4.250   0.8222   0.01189   0.00719  -0.0753   0.6728   0.8370
   4.500   0.8482   0.01179   0.00711  -0.0752   0.6673   0.8378
   4.750   0.8720   0.01167   0.00705  -0.0747   0.6601   0.8388
   5.000   0.8987   0.01156   0.00693  -0.0747   0.6536   0.8399
   5.250   0.9209   0.01147   0.00692  -0.0738   0.6446   0.8412
   5.500   0.9456   0.01138   0.00684  -0.0735   0.6355   0.8422
   5.750   0.9695   0.01130   0.00677  -0.0731   0.6244   0.8432
   6.000   0.9915   0.01126   0.00674  -0.0723   0.6102   0.8443
   6.250   1.0121   0.01127   0.00673  -0.0712   0.5923   0.8454
   6.500   1.0308   0.01135   0.00678  -0.0698   0.5714   0.8465
   6.750   1.0457   0.01156   0.00687  -0.0677   0.5487   0.8476
   7.000   1.0540   0.01171   0.00697  -0.0642   0.5252   0.8489
   7.250   1.0597   0.01203   0.00719  -0.0602   0.5010   0.8501
   7.500   1.0663   0.01248   0.00756  -0.0567   0.4741   0.8513
   7.750   1.0711   0.01305   0.00802  -0.0530   0.4459   0.8525
   8.000   1.0738   0.01375   0.00861  -0.0491   0.4166   0.8538
   8.250   1.0759   0.01457   0.00929  -0.0455   0.3875   0.8551
   8.500   1.0804   0.01541   0.01003  -0.0424   0.3615   0.8564
   8.750   1.0870   0.01625   0.01079  -0.0399   0.3366   0.8577
   9.000   1.0925   0.01723   0.01166  -0.0373   0.3130   0.8592
   9.250   1.0984   0.01826   0.01259  -0.0350   0.2857   0.8606
   9.500   1.1059   0.01930   0.01352  -0.0330   0.2628   0.8616
   9.750   1.1140   0.02035   0.01448  -0.0312   0.2403   0.8624
  10.000   1.1210   0.02144   0.01547  -0.0293   0.2186   0.8633
  10.250   1.1277   0.02255   0.01649  -0.0273   0.1954   0.8642
  10.500   1.1349   0.02368   0.01754  -0.0255   0.1760   0.8652
  10.750   1.1429   0.02481   0.01859  -0.0239   0.1563   0.8661
  11.000   1.1498   0.02605   0.01974  -0.0223   0.1366   0.8671
  11.250   1.1587   0.02720   0.02084  -0.0209   0.1217   0.8681
  11.500   1.1666   0.02846   0.02204  -0.0195   0.1069   0.8692
  11.750   1.1754   0.02969   0.02323  -0.0183   0.0938   0.8704
  12.000   1.1834   0.03103   0.02452  -0.0171   0.0810   0.8715
  12.250   1.1922   0.03236   0.02581  -0.0160   0.0698   0.8725
  12.500   1.2001   0.03380   0.02721  -0.0150   0.0587   0.8735
  12.750   1.2063   0.03541   0.02877  -0.0139   0.0455   0.8744
  13.000   1.2074   0.03749   0.03075  -0.0125   0.0307   0.8752
  13.500   1.2154   0.04143   0.03465  -0.0105   0.0194   0.8768
  13.750   1.2217   0.04329   0.03657  -0.0098   0.0175   0.8776
  14.000   1.2279   0.04512   0.03847  -0.0091   0.0163   0.8785
  14.250   1.2323   0.04718   0.04060  -0.0084   0.0156   0.8794
  14.500   1.2347   0.04952   0.04302  -0.0077   0.0148   0.8803
  14.750   1.2399   0.05164   0.04525  -0.0073   0.0144   0.8812
  15.000   1.2441   0.05391   0.04762  -0.0070   0.0140   0.8823
  15.250   1.2470   0.05640   0.05020  -0.0067   0.0135   0.8834
  15.500   1.2489   0.05908   0.05297  -0.0066   0.0132   0.8846
  15.750   1.2502   0.06191   0.05589  -0.0066   0.0129   0.8857
  16.000   1.2500   0.06500   0.05908  -0.0068   0.0127   0.8866
  16.250   1.2471   0.06853   0.06269  -0.0071   0.0124   0.8875
  16.500   1.2443   0.07215   0.06641  -0.0076   0.0123   0.8883
  16.750   1.2381   0.07632   0.07067  -0.0083   0.0120   0.8891
  17.000   1.2391   0.07964   0.07410  -0.0091   0.0119   0.8899
  17.250   1.2393   0.08312   0.07770  -0.0100   0.0118   0.8908
  17.500   1.2398   0.08664   0.08132  -0.0110   0.0116   0.8915
  17.750   1.2395   0.09034   0.08512  -0.0122   0.0114   0.8923
  18.000   1.2391   0.09405   0.08895  -0.0134   0.0112   0.8932
  18.250   1.2383   0.09784   0.09285  -0.0147   0.0111   0.8942
  18.500   1.2376   0.10165   0.09676  -0.0161   0.0109   0.8951
  18.750   1.2364   0.10557   0.10079  -0.0177   0.0107   0.8961
  19.000   1.2356   0.10950   0.10482  -0.0193   0.0106   0.8971
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