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EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il)
Reynolds number: 200,000
Max Cl/Cd: 51.66 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e874-il-200000.txt
Download as CSV file: xf-e874-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 874 HYDROFOIL AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4691   0.10438   0.10104  -0.0056   1.0000   0.0450
 -10.000  -0.4768   0.09955   0.09624  -0.0088   1.0000   0.0470
  -9.750  -0.5740   0.10450   0.10097  -0.0021   1.0000   0.0412
  -9.500  -0.5730   0.10065   0.09714  -0.0038   1.0000   0.0421
  -9.250  -0.5745   0.09634   0.09286  -0.0060   1.0000   0.0444
  -9.000  -0.5787   0.09151   0.08810  -0.0095   1.0000   0.0461
  -6.250  -0.6000   0.03460   0.02937  -0.0215   1.0000   0.0343
  -6.000  -0.5883   0.03086   0.02519  -0.0192   1.0000   0.0337
  -5.750  -0.5751   0.02636   0.02008  -0.0163   1.0000   0.0290
  -5.500  -0.5512   0.02526   0.01843  -0.0139   1.0000   0.0250
  -5.250  -0.5325   0.02192   0.01477  -0.0120   1.0000   0.0237
  -5.000  -0.5115   0.01967   0.01224  -0.0103   1.0000   0.0231
  -4.750  -0.4898   0.01790   0.01030  -0.0086   1.0000   0.0229
  -4.500  -0.4686   0.01645   0.00873  -0.0070   1.0000   0.0230
  -4.250  -0.4479   0.01529   0.00748  -0.0053   1.0000   0.0236
  -4.000  -0.4269   0.01435   0.00642  -0.0036   1.0000   0.0247
  -3.750  -0.4068   0.01315   0.00502  -0.0017   1.0000   0.0314
  -3.500  -0.3898   0.01144   0.00416   0.0002   1.0000   0.1944
  -3.250  -0.3684   0.01105   0.00410   0.0011   1.0000   0.2725
  -3.000  -0.3468   0.01066   0.00386   0.0022   1.0000   0.3184
  -2.750  -0.3256   0.01021   0.00360   0.0035   1.0000   0.3710
  -2.500  -0.3056   0.00972   0.00341   0.0050   1.0000   0.4425
  -2.250  -0.2872   0.00921   0.00325   0.0068   1.0000   0.5387
  -2.000  -0.2708   0.00866   0.00320   0.0094   1.0000   0.6580
  -1.750  -0.1716   0.00812   0.00335  -0.0044   1.0000   0.9263
  -1.500  -0.0879   0.00834   0.00334  -0.0160   1.0000   0.9959
  -1.250  -0.0577   0.00831   0.00322  -0.0169   1.0000   1.0000
  -1.000  -0.0400   0.00831   0.00316  -0.0150   1.0000   1.0000
  -0.750  -0.0230   0.00834   0.00315  -0.0132   1.0000   1.0000
  -0.500  -0.0074   0.00842   0.00320  -0.0111   1.0000   1.0000
  -0.250   0.0476   0.00839   0.00314  -0.0171   0.9874   1.0000
   0.000   0.0964   0.00825   0.00299  -0.0217   0.9620   1.0000
   0.250   0.1533   0.00811   0.00285  -0.0278   0.9352   1.0000
   0.500   0.2226   0.00794   0.00263  -0.0365   0.8926   1.0000
   0.750   0.2741   0.00794   0.00245  -0.0411   0.8290   1.0000
   1.000   0.3008   0.00815   0.00243  -0.0405   0.7762   1.0000
   1.250   0.3239   0.00838   0.00251  -0.0392   0.7362   1.0000
   1.500   0.3467   0.00861   0.00259  -0.0380   0.7032   1.0000
   1.750   0.3699   0.00884   0.00271  -0.0369   0.6760   1.0000
   2.000   0.3935   0.00906   0.00286  -0.0360   0.6530   1.0000
   2.250   0.4173   0.00929   0.00304  -0.0350   0.6328   1.0000
   2.500   0.4414   0.00952   0.00328  -0.0342   0.6145   1.0000
   2.750   0.4655   0.00973   0.00351  -0.0333   0.5967   1.0000
   3.000   0.4893   0.00994   0.00374  -0.0324   0.5785   1.0000
   3.250   0.5114   0.01011   0.00388  -0.0309   0.5498   1.0000
   3.500   0.5290   0.01024   0.00379  -0.0285   0.4787   1.0000
   3.750   0.5465   0.01068   0.00389  -0.0263   0.3704   1.0000
   4.000   0.5499   0.01375   0.00528  -0.0223   0.0326   1.0000
   4.250   0.5680   0.01496   0.00665  -0.0201   0.0272   1.0000
   4.500   0.5871   0.01600   0.00781  -0.0182   0.0257   1.0000
   4.750   0.6060   0.01726   0.00914  -0.0161   0.0245   1.0000
   5.000   0.6265   0.01823   0.01012  -0.0146   0.0199   1.0000
   5.250   0.6463   0.01990   0.01184  -0.0129   0.0189   1.0000
   5.500   0.6684   0.02171   0.01379  -0.0113   0.0189   1.0000
   5.750   0.6923   0.02383   0.01620  -0.0095   0.0205   1.0000
   6.000   0.7144   0.02704   0.01991  -0.0073   0.0238   1.0000
  12.500   0.6945   0.14496   0.14128  -0.0257   0.0321   1.0000
  12.750   0.6982   0.14888   0.14518  -0.0270   0.0310   1.0000
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