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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 50,000
Max Cl/Cd: 26.08 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e818-il-50000-n5.txt
Download as CSV file: xf-e818-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 818 HYDROFOIL AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4687   0.09941   0.09245  -0.0444   1.0000   0.0196
  -9.250  -0.4743   0.09552   0.08864  -0.0449   1.0000   0.0194
  -9.000  -0.4813   0.09149   0.08471  -0.0454   1.0000   0.0191
  -8.750  -0.4896   0.08751   0.08081  -0.0458   1.0000   0.0187
  -8.500  -0.5007   0.08336   0.07675  -0.0463   1.0000   0.0185
  -8.250  -0.5146   0.07938   0.07285  -0.0467   1.0000   0.0182
  -8.000  -0.5315   0.07581   0.06933  -0.0467   1.0000   0.0180
  -7.750  -0.5508   0.07222   0.06579  -0.0470   1.0000   0.0179
  -7.500  -0.5655   0.06806   0.06160  -0.0489   1.0000   0.0177
  -7.250  -0.5764   0.06390   0.05733  -0.0502   1.0000   0.0175
  -7.000  -0.5819   0.05972   0.05295  -0.0514   1.0000   0.0173
  -6.750  -0.5816   0.05545   0.04838  -0.0527   1.0000   0.0171
  -6.500  -0.5751   0.05127   0.04382  -0.0540   1.0000   0.0169
  -6.250  -0.5630   0.04717   0.03926  -0.0551   1.0000   0.0168
  -6.000  -0.5464   0.04361   0.03520  -0.0559   1.0000   0.0168
  -5.750  -0.5263   0.04038   0.03145  -0.0563   1.0000   0.0177
  -5.500  -0.5044   0.03775   0.02833  -0.0564   1.0000   0.0187
  -5.250  -0.4814   0.03573   0.02582  -0.0560   1.0000   0.0206
  -5.000  -0.4592   0.03338   0.02319  -0.0556   1.0000   0.0230
  -4.750  -0.4370   0.03152   0.02113  -0.0553   1.0000   0.0260
  -4.500  -0.4135   0.02996   0.01931  -0.0548   1.0000   0.0286
  -4.250  -0.3878   0.02843   0.01727  -0.0548   1.0000   0.0311
  -4.000  -0.3592   0.02678   0.01530  -0.0558   1.0000   0.0357
  -3.750  -0.3268   0.02438   0.01308  -0.0582   1.0000   0.0755
  -3.500  -0.3010   0.02326   0.01423  -0.0589   1.0000   0.4825
  -3.250  -0.2765   0.02307   0.01364  -0.0581   1.0000   0.5013
  -3.000  -0.2519   0.02291   0.01316  -0.0577   1.0000   0.5210
  -2.750  -0.2282   0.02279   0.01281  -0.0570   1.0000   0.5397
  -2.500  -0.2039   0.02270   0.01248  -0.0566   1.0000   0.5599
  -2.250  -0.1810   0.02264   0.01227  -0.0558   1.0000   0.5787
  -2.000  -0.1574   0.02260   0.01207  -0.0553   1.0000   0.5995
  -1.750  -0.1351   0.02259   0.01180  -0.0545   1.0000   0.6193
  -1.500  -0.1124   0.02260   0.01171  -0.0538   1.0000   0.6403
  -1.250  -0.0905   0.02262   0.01168  -0.0529   1.0000   0.6612
  -1.000  -0.0691   0.02266   0.01168  -0.0520   1.0000   0.6826
  -0.750  -0.0477   0.02272   0.01171  -0.0511   1.0000   0.7055
  -0.500  -0.0274   0.02277   0.01177  -0.0499   1.0000   0.7285
  -0.250  -0.0080   0.02283   0.01179  -0.0486   1.0000   0.7527
   0.000   0.0115   0.02289   0.01188  -0.0473   0.9995   0.7793
   0.250   0.0378   0.02310   0.01213  -0.0473   0.9948   0.8103
   0.500   0.0617   0.02319   0.01230  -0.0468   0.9897   0.8461
   0.750   0.0877   0.02324   0.01246  -0.0469   0.9842   0.8982
   1.000   0.1221   0.02324   0.01251  -0.0494   0.9769   1.0000
   1.250   0.1598   0.02375   0.01294  -0.0527   0.9719   1.0000
   1.500   0.1972   0.02431   0.01344  -0.0557   0.9670   1.0000
   1.750   0.2308   0.02477   0.01388  -0.0579   0.9606   1.0000
   2.000   0.2687   0.02538   0.01452  -0.0608   0.9552   1.0000
   2.250   0.3002   0.02581   0.01502  -0.0625   0.9475   1.0000
   2.500   0.3361   0.02638   0.01568  -0.0649   0.9409   1.0000
   2.750   0.3696   0.02688   0.01653  -0.0667   0.9329   1.0000
   3.000   0.4024   0.02737   0.01720  -0.0684   0.9243   1.0000
   3.250   0.4409   0.02791   0.01798  -0.0710   0.9164   1.0000
   3.500   0.4742   0.02834   0.01868  -0.0725   0.9059   1.0000
   3.750   0.5078   0.02873   0.01940  -0.0740   0.8944   1.0000
   4.000   0.5433   0.02905   0.02026  -0.0756   0.8819   1.0000
   4.250   0.5820   0.02923   0.02091  -0.0773   0.8676   1.0000
   4.500   0.6207   0.02911   0.02140  -0.0785   0.8489   1.0000
   4.750   0.6903   0.02647   0.01466  -0.0708   0.0620   1.0000
   5.000   0.7128   0.02837   0.01666  -0.0697   0.0446   1.0000
   5.250   0.7404   0.03050   0.01890  -0.0693   0.0382   1.0000
   5.500   0.7766   0.03226   0.02096  -0.0700   0.0302   1.0000
   5.750   0.8193   0.03517   0.02402  -0.0717   0.0256   1.0000
   6.000   0.8592   0.03826   0.02752  -0.0725   0.0245   1.0000
   6.250   0.8910   0.04157   0.03129  -0.0723   0.0239   1.0000
   6.500   0.9162   0.04504   0.03526  -0.0711   0.0235   1.0000
   6.750   0.9357   0.04871   0.03968  -0.0694   0.0234   1.0000
   7.000   0.9504   0.05243   0.04389  -0.0673   0.0234   1.0000
   7.250   0.9610   0.05622   0.04814  -0.0649   0.0235   1.0000
   7.500   0.9678   0.06012   0.05245  -0.0624   0.0237   1.0000
   7.750   0.9711   0.06405   0.05675  -0.0600   0.0240   1.0000
   8.000   0.9710   0.06802   0.06106  -0.0575   0.0243   1.0000
   8.250   0.9676   0.07201   0.06533  -0.0551   0.0245   1.0000
   8.500   0.9612   0.07594   0.06951  -0.0528   0.0248   1.0000
   8.750   0.9509   0.07973   0.07349  -0.0505   0.0251   1.0000
   9.000   0.9384   0.08351   0.07743  -0.0485   0.0253   1.0000
   9.250   0.9248   0.08754   0.08159  -0.0473   0.0255   1.0000
   9.500   0.9109   0.09193   0.08609  -0.0471   0.0258   1.0000
   9.750   0.8980   0.09668   0.09093  -0.0478   0.0260   1.0000
  10.000   0.8861   0.10184   0.09615  -0.0494   0.0263   1.0000
  10.250   0.8777   0.10735   0.10168  -0.0514   0.0266   1.0000
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