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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 500,000
Max Cl/Cd: 128.58 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e66-il-500000.txt
Download as CSV file: xf-e66-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3239   0.06972   0.06762  -0.0707   0.9766   0.0238
  -7.500  -0.3367   0.03468   0.03170  -0.1124   0.9614   0.0174
  -7.250  -0.3220   0.02317   0.01890  -0.1181   0.9562   0.0134
  -7.000  -0.2958   0.02080   0.01617  -0.1191   0.9523   0.0137
  -6.750  -0.2639   0.01891   0.01398  -0.1208   0.9503   0.0142
  -6.500  -0.2300   0.01741   0.01223  -0.1225   0.9489   0.0150
  -6.250  -0.1949   0.01630   0.01091  -0.1243   0.9478   0.0158
  -6.000  -0.1600   0.01469   0.00910  -0.1263   0.9469   0.0170
  -5.750  -0.1237   0.01394   0.00833  -0.1285   0.9462   0.0191
  -5.250  -0.0684   0.01237   0.00657  -0.1288   0.9378   0.0236
  -5.000  -0.0325   0.01177   0.00593  -0.1306   0.9365   0.0276
  -4.750   0.0046   0.01110   0.00522  -0.1327   0.9354   0.0337
  -4.500   0.0420   0.01056   0.00465  -0.1348   0.9342   0.0427
  -4.250   0.0793   0.01001   0.00416  -0.1369   0.9330   0.0641
  -4.000   0.1063   0.00965   0.00388  -0.1368   0.9278   0.0910
  -3.750   0.1384   0.00929   0.00359  -0.1378   0.9242   0.1189
  -3.500   0.1738   0.00891   0.00332  -0.1395   0.9216   0.1522
  -3.250   0.2100   0.00857   0.00306  -0.1414   0.9193   0.1898
  -3.000   0.2373   0.00832   0.00292  -0.1413   0.9133   0.2289
  -2.750   0.2693   0.00803   0.00275  -0.1423   0.9086   0.2777
  -2.500   0.3038   0.00775   0.00258  -0.1438   0.9050   0.3242
  -2.250   0.3307   0.00758   0.00250  -0.1436   0.8981   0.3659
  -2.000   0.3621   0.00737   0.00238  -0.1443   0.8927   0.4103
  -1.750   0.3916   0.00720   0.00232  -0.1447   0.8865   0.4585
  -1.500   0.4203   0.00704   0.00226  -0.1448   0.8795   0.5066
  -1.250   0.4498   0.00689   0.00222  -0.1451   0.8729   0.5551
  -1.000   0.4775   0.00677   0.00220  -0.1450   0.8650   0.6001
  -0.750   0.5057   0.00668   0.00219  -0.1449   0.8573   0.6439
  -0.500   0.5336   0.00659   0.00217  -0.1448   0.8491   0.6854
  -0.250   0.5598   0.00652   0.00219  -0.1443   0.8401   0.7259
   0.000   0.5874   0.00646   0.00219  -0.1440   0.8318   0.7648
   0.250   0.6122   0.00642   0.00222  -0.1431   0.8218   0.8012
   0.500   0.6366   0.00639   0.00225  -0.1421   0.8119   0.8361
   0.750   0.6606   0.00637   0.00226  -0.1410   0.8021   0.8713
   1.000   0.6817   0.00633   0.00227  -0.1392   0.7911   0.9073
   1.250   0.7026   0.00627   0.00223  -0.1373   0.7795   0.9529
   1.500   0.7353   0.00627   0.00220  -0.1383   0.7674   1.0000
   1.750   0.7626   0.00636   0.00222  -0.1382   0.7548   1.0000
   2.000   0.7895   0.00646   0.00227  -0.1380   0.7415   1.0000
   2.250   0.8160   0.00657   0.00232  -0.1377   0.7276   1.0000
   2.500   0.8422   0.00669   0.00239  -0.1373   0.7127   1.0000
   2.750   0.8679   0.00683   0.00246  -0.1368   0.6967   1.0000
   3.000   0.8932   0.00698   0.00256  -0.1362   0.6795   1.0000
   3.250   0.9180   0.00715   0.00266  -0.1355   0.6611   1.0000
   3.500   0.9425   0.00733   0.00278  -0.1348   0.6416   1.0000
   3.750   0.9666   0.00753   0.00292  -0.1340   0.6208   1.0000
   4.000   0.9902   0.00776   0.00307  -0.1332   0.5991   1.0000
   4.250   1.0132   0.00801   0.00324  -0.1322   0.5747   1.0000
   4.500   1.0357   0.00829   0.00343  -0.1311   0.5479   1.0000
   4.750   1.0573   0.00861   0.00365  -0.1299   0.5186   1.0000
   5.000   1.0782   0.00898   0.00389  -0.1285   0.4869   1.0000
   5.250   1.0989   0.00938   0.00416  -0.1272   0.4549   1.0000
   5.500   1.1193   0.00980   0.00445  -0.1258   0.4205   1.0000
   5.750   1.1394   0.01025   0.00479  -0.1244   0.3870   1.0000
   6.000   1.1584   0.01078   0.00515  -0.1229   0.3489   1.0000
   6.250   1.1759   0.01143   0.00557  -0.1211   0.3038   1.0000
   6.500   1.1931   0.01210   0.00602  -0.1193   0.2601   1.0000
   6.750   1.2106   0.01277   0.00649  -0.1176   0.2225   1.0000
   7.000   1.2283   0.01340   0.00698  -0.1160   0.1894   1.0000
   7.250   1.2450   0.01405   0.00748  -0.1141   0.1596   1.0000
   7.500   1.2616   0.01468   0.00800  -0.1122   0.1343   1.0000
   7.750   1.2774   0.01536   0.00856  -0.1102   0.1115   1.0000
   8.000   1.2930   0.01605   0.00914  -0.1083   0.0904   1.0000
   8.250   1.3083   0.01675   0.00978  -0.1062   0.0723   1.0000
   8.500   1.3226   0.01752   0.01046  -0.1041   0.0555   1.0000
   8.750   1.3350   0.01843   0.01128  -0.1017   0.0398   1.0000
   9.000   1.3470   0.01937   0.01219  -0.0992   0.0301   1.0000
   9.250   1.3598   0.02025   0.01307  -0.0969   0.0251   1.0000
   9.500   1.3717   0.02119   0.01408  -0.0944   0.0220   1.0000
   9.750   1.3856   0.02198   0.01492  -0.0924   0.0198   1.0000
  10.000   1.3939   0.02318   0.01619  -0.0897   0.0178   1.0000
  10.250   1.4013   0.02446   0.01757  -0.0869   0.0166   1.0000
  10.500   1.4130   0.02543   0.01864  -0.0848   0.0154   1.0000
  10.750   1.4237   0.02649   0.01977  -0.0827   0.0143   1.0000
  11.000   1.4302   0.02790   0.02123  -0.0803   0.0132   1.0000
  11.250   1.4264   0.03021   0.02367  -0.0768   0.0122   1.0000
  11.500   1.4366   0.03142   0.02499  -0.0750   0.0117   1.0000
  11.750   1.4438   0.03294   0.02662  -0.0731   0.0111   1.0000
  12.000   1.4497   0.03461   0.02840  -0.0711   0.0105   1.0000
  12.250   1.4546   0.03642   0.03030  -0.0693   0.0100   1.0000
  12.500   1.4580   0.03841   0.03239  -0.0676   0.0096   1.0000
  12.750   1.4573   0.04094   0.03503  -0.0657   0.0092   1.0000
  13.000   1.4496   0.04448   0.03872  -0.0636   0.0088   1.0000
  13.250   1.4486   0.04743   0.04183  -0.0622   0.0086   1.0000
  13.500   1.4514   0.04987   0.04442  -0.0612   0.0084   1.0000
  13.750   1.4523   0.05265   0.04736  -0.0603   0.0082   1.0000
  14.000   1.4519   0.05569   0.05056  -0.0596   0.0080   1.0000
  14.250   1.4503   0.05900   0.05403  -0.0592   0.0078   1.0000
  14.500   1.4476   0.06253   0.05773  -0.0590   0.0076   1.0000
  14.750   1.4440   0.06633   0.06168  -0.0591   0.0074   1.0000
  15.000   1.4403   0.07025   0.06575  -0.0596   0.0072   1.0000
  15.250   1.4355   0.07445   0.07009  -0.0604   0.0071   1.0000
  15.500   1.4296   0.07902   0.07480  -0.0615   0.0069   1.0000
  15.750   1.4234   0.08380   0.07972  -0.0630   0.0068   1.0000
  16.000   1.4160   0.08897   0.08502  -0.0649   0.0067   1.0000
  16.250   1.4071   0.09457   0.09076  -0.0671   0.0066   1.0000
  16.500   1.3973   0.10053   0.09689  -0.0697   0.0065   1.0000
  16.750   1.3865   0.10687   0.10338  -0.0727   0.0064   1.0000
  17.000   1.3745   0.11370   0.11036  -0.0762   0.0064   1.0000
  17.250   1.3613   0.12098   0.11781  -0.0802   0.0063   1.0000
  17.500   1.3473   0.12867   0.12567  -0.0847   0.0063   1.0000
  17.750   1.3333   0.13667   0.13384  -0.0896   0.0063   1.0000
  18.000   1.3191   0.14509   0.14243  -0.0950   0.0063   1.0000
  18.250   1.3031   0.15425   0.15177  -0.1010   0.0064   1.0000
  18.500   1.2835   0.16488   0.16258  -0.1082   0.0065   1.0000
  18.750   1.2387   0.18438   0.18243  -0.1213   0.0068   1.0000
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