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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 500,000
Max Cl/Cd: 96.07 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e818-il-500000-n5.txt
Download as CSV file: xf-e818-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3912   0.08269   0.08040  -0.0636   0.9875   0.0102
  -9.000  -0.3860   0.07544   0.07314  -0.0695   0.9849   0.0102
  -8.750  -0.3821   0.06749   0.06513  -0.0783   0.9822   0.0102
  -8.500  -0.3847   0.06047   0.05803  -0.0866   0.9756   0.0102
  -8.250  -0.3843   0.05382   0.05122  -0.0975   0.9692   0.0102
  -8.000  -0.3831   0.04887   0.04607  -0.1050   0.9597   0.0102
  -7.750  -0.3692   0.04384   0.04074  -0.1116   0.9563   0.0103
  -7.500  -0.3580   0.04006   0.03668  -0.1142   0.9501   0.0103
  -7.250  -0.3402   0.03618   0.03247  -0.1170   0.9462   0.0103
  -7.000  -0.3177   0.03251   0.02846  -0.1196   0.9436   0.0103
  -6.750  -0.3077   0.02511   0.02062  -0.1209   0.9375   0.0088
  -6.500  -0.2842   0.01984   0.01473  -0.1211   0.9338   0.0053
  -6.250  -0.2534   0.01868   0.01334  -0.1213   0.9319   0.0040
  -6.000  -0.2244   0.01725   0.01176  -0.1220   0.9302   0.0035
  -5.750  -0.2014   0.01510   0.00934  -0.1215   0.9265   0.0033
  -5.500  -0.1758   0.01365   0.00774  -0.1215   0.9235   0.0031
  -5.250  -0.1482   0.01242   0.00637  -0.1219   0.9210   0.0029
  -5.000  -0.1188   0.01142   0.00521  -0.1227   0.9190   0.0028
  -4.750  -0.0884   0.01065   0.00427  -0.1235   0.9172   0.0028
  -4.500  -0.0611   0.01016   0.00362  -0.1236   0.9143   0.0027
  -4.250  -0.0328   0.00982   0.00314  -0.1239   0.9118   0.0027
  -4.000  -0.0040   0.00958   0.00277  -0.1242   0.9097   0.0028
  -3.750   0.0252   0.00941   0.00251  -0.1246   0.9078   0.0031
  -3.500   0.0546   0.00928   0.00228  -0.1250   0.9061   0.0033
  -3.250   0.0846   0.00834   0.00184  -0.1264   0.9045   0.1570
  -3.000   0.1123   0.00795   0.00172  -0.1269   0.9021   0.2310
  -2.500   0.1687   0.00726   0.00170  -0.1281   0.8978   0.4020
  -2.250   0.1974   0.00721   0.00167  -0.1285   0.8958   0.4151
  -2.000   0.2264   0.00716   0.00162  -0.1289   0.8939   0.4279
  -1.750   0.2556   0.00712   0.00160  -0.1293   0.8923   0.4405
  -1.500   0.2847   0.00709   0.00159  -0.1298   0.8907   0.4539
  -1.000   0.3400   0.00705   0.00165  -0.1300   0.8856   0.4794
  -0.750   0.3684   0.00702   0.00167  -0.1302   0.8831   0.4927
  -0.500   0.3972   0.00700   0.00170  -0.1305   0.8809   0.5059
   0.000   0.4537   0.00696   0.00179  -0.1309   0.8751   0.5333
   0.250   0.4812   0.00693   0.00184  -0.1309   0.8709   0.5472
   0.500   0.5100   0.00690   0.00187  -0.1312   0.8667   0.5612
   0.750   0.5372   0.00688   0.00200  -0.1310   0.8612   0.5748
   1.000   0.5649   0.00684   0.00206  -0.1310   0.8547   0.5884
   1.250   0.5918   0.00681   0.00212  -0.1307   0.8464   0.6019
   1.500   0.6181   0.00675   0.00213  -0.1302   0.8320   0.6155
   1.750   0.6427   0.00669   0.00207  -0.1292   0.8007   0.6288
   2.000   0.6603   0.00695   0.00197  -0.1265   0.6927   0.6419
   2.250   0.6503   0.00922   0.00269  -0.1191   0.3734   0.6527
   2.500   0.6563   0.01115   0.00342  -0.1156   0.0996   0.6652
   2.750   0.6755   0.01210   0.00408  -0.1140   0.0061   0.6790
   3.000   0.7003   0.01244   0.00459  -0.1133   0.0055   0.6940
   3.250   0.7242   0.01290   0.00523  -0.1124   0.0053   0.7090
   3.500   0.7476   0.01339   0.00585  -0.1115   0.0047   0.7244
   3.750   0.7722   0.01367   0.00618  -0.1110   0.0033   0.7405
   4.250   0.8123   0.01565   0.00845  -0.1079   0.0020   0.7730
   4.500   0.8353   0.01621   0.00914  -0.1069   0.0018   0.7911
   4.750   0.8573   0.01720   0.01030  -0.1056   0.0016   0.8098
   5.000   0.8799   0.01861   0.01192  -0.1043   0.0014   0.8293
   5.500   0.9283   0.02264   0.01653  -0.1016   0.0013   0.8745
   5.750   0.9485   0.02516   0.01953  -0.0992   0.0013   0.9067
   6.000   0.9662   0.02810   0.02290  -0.0963   0.0013   1.0000
   6.250   0.9854   0.03184   0.02703  -0.0939   0.0014   1.0000
   6.500   1.0007   0.03589   0.03148  -0.0911   0.0014   1.0000
   6.750   1.0123   0.04013   0.03608  -0.0880   0.0015   1.0000
   7.000   1.0205   0.04454   0.04083  -0.0847   0.0016   1.0000
   7.250   1.0250   0.04908   0.04569  -0.0813   0.0017   1.0000
   7.500   1.0251   0.05382   0.05071  -0.0778   0.0018   1.0000
   7.750   1.0186   0.05880   0.05596  -0.0741   0.0019   1.0000
   8.000   1.0016   0.06377   0.06113  -0.0703   0.0020   1.0000
   8.250   0.9979   0.06696   0.06449  -0.0675   0.0020   1.0000
   8.500   0.9900   0.06973   0.06738  -0.0642   0.0020   1.0000
   8.750   0.9788   0.07284   0.07061  -0.0613   0.0021   1.0000
   9.000   0.9652   0.07649   0.07438  -0.0592   0.0021   1.0000
   9.250   0.9513   0.08059   0.07858  -0.0583   0.0021   1.0000
   9.500   0.9373   0.08530   0.08339  -0.0587   0.0021   1.0000
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