Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E838 HYDROFOIL AIRFOIL (e838-il)
Reynolds number: 50,000
Max Cl/Cd: 16.41 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e838-il-50000-n5.txt
Download as CSV file: xf-e838-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E838 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
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.6768   0.11524   0.10824  -0.0353   1.0000   0.0433
 -15.250  -0.7020   0.10634   0.09919  -0.0402   1.0000   0.0427
 -15.000  -0.7256   0.09865   0.09131  -0.0441   1.0000   0.0424
 -14.750  -0.7451   0.09215   0.08461  -0.0469   1.0000   0.0422
 -14.500  -0.7633   0.08632   0.07853  -0.0491   1.0000   0.0426
 -14.250  -0.7759   0.08139   0.07335  -0.0504   1.0000   0.0429
 -14.000  -0.7870   0.07678   0.06844  -0.0513   1.0000   0.0438
 -13.750  -0.7907   0.07281   0.06416  -0.0517   1.0000   0.0444
 -13.500  -0.7893   0.06922   0.06020  -0.0517   1.0000   0.0455
 -13.250  -0.7748   0.06679   0.05769  -0.0515   1.0000   0.0480
 -13.000  -0.7654   0.06452   0.05533  -0.0514   1.0000   0.0513
 -12.750  -0.7501   0.06237   0.05290  -0.0510   1.0000   0.0552
 -12.500  -0.7210   0.06125   0.05168  -0.0500   1.0000   0.0596
 -12.250  -0.7055   0.05969   0.05004  -0.0495   1.0000   0.0653
 -12.000  -0.6893   0.05823   0.04852  -0.0488   1.0000   0.0719
 -11.750  -0.6752   0.05674   0.04698  -0.0479   1.0000   0.0795
 -11.500  -0.6659   0.05496   0.04528  -0.0472   1.0000   0.0882
 -11.250  -0.6594   0.05300   0.04339  -0.0466   1.0000   0.1000
 -11.000  -0.6553   0.05094   0.04142  -0.0458   1.0000   0.1139
 -10.750  -0.6545   0.04869   0.03936  -0.0450   1.0000   0.1335
 -10.500  -0.6569   0.04634   0.03729  -0.0439   1.0000   0.1576
 -10.250  -0.6621   0.04394   0.03525  -0.0427   1.0000   0.1917
 -10.000  -0.6686   0.04176   0.03353  -0.0409   1.0000   0.2360
  -9.750  -0.6682   0.04079   0.03324  -0.0383   1.0000   0.3033
  -9.500  -0.6437   0.04275   0.03563  -0.0352   1.0000   0.3805
  -9.250  -0.6298   0.04381   0.03667  -0.0326   1.0000   0.4184
  -9.000  -0.6340   0.04397   0.03678  -0.0289   1.0000   0.4431
  -8.750  -0.6326   0.04459   0.03731  -0.0256   0.9911   0.4653
  -8.500  -0.5949   0.04628   0.03867  -0.0263   0.9778   0.4903
  -8.250  -0.5685   0.04653   0.03863  -0.0274   0.9655   0.5136
  -8.000  -0.5255   0.04784   0.03960  -0.0287   0.9569   0.5296
  -7.750  -0.4912   0.04819   0.03963  -0.0301   0.9477   0.5441
  -7.500  -0.4582   0.04807   0.03922  -0.0318   0.9399   0.5577
  -7.250  -0.4256   0.04809   0.03898  -0.0331   0.9311   0.5685
  -7.000  -0.3854   0.04813   0.03871  -0.0352   0.9249   0.5770
  -6.750  -0.3655   0.04754   0.03793  -0.0355   0.9157   0.5880
  -6.500  -0.3514   0.04675   0.03696  -0.0353   0.9071   0.5998
  -6.250  -0.3107   0.04686   0.03684  -0.0371   0.9008   0.6046
  -5.750  -0.2657   0.04601   0.03564  -0.0374   0.8864   0.6203
  -5.500  -0.2584   0.04523   0.03472  -0.0360   0.8788   0.6300
  -5.250  -0.2274   0.04511   0.03446  -0.0367   0.8725   0.6347
  -5.000  -0.2233   0.04432   0.03355  -0.0348   0.8658   0.6443
  -4.750  -0.1939   0.04424   0.03334  -0.0354   0.8595   0.6483
  -4.500  -0.1801   0.04372   0.03270  -0.0344   0.8536   0.6556
  -4.250  -0.1652   0.04339   0.03229  -0.0333   0.8472   0.6615
  -4.000  -0.1431   0.04312   0.03193  -0.0331   0.8415   0.6666
  -3.750  -0.1419   0.04250   0.03122  -0.0304   0.8356   0.6746
  -3.500  -0.1176   0.04244   0.03109  -0.0304   0.8298   0.6784
  -3.250  -0.1070   0.04202   0.03060  -0.0287   0.8244   0.6849
  -3.000  -0.0998   0.04171   0.03025  -0.0266   0.8185   0.6906
  -2.750  -0.0782   0.04160   0.03008  -0.0263   0.8132   0.6948
  -2.500  -0.0884   0.04098   0.02939  -0.0217   0.8078   0.7034
  -2.250  -0.0666   0.04110   0.02950  -0.0214   0.8020   0.7066
  -2.000  -0.0496   0.04097   0.02933  -0.0204   0.7970   0.7111
  -1.750  -0.0552   0.04043   0.02874  -0.0164   0.7921   0.7189
  -1.500  -0.0402   0.04066   0.02897  -0.0150   0.7858   0.7224
  -1.250  -0.0260   0.04051   0.02879  -0.0136   0.7812   0.7274
  -1.000  -0.0301   0.04017   0.02841  -0.0097   0.7760   0.7344
  -0.750  -0.0186   0.04040   0.02866  -0.0078   0.7698   0.7382
  -0.500  -0.0068   0.04022   0.02846  -0.0060   0.7655   0.7436
  -0.250  -0.0106   0.04010   0.02832  -0.0020   0.7598   0.7499
   0.000  -0.0001   0.04031   0.02856   0.0000   0.7540   0.7540
   0.250   0.0105   0.04010   0.02832   0.0020   0.7498   0.7598
   0.500   0.0066   0.04022   0.02846   0.0060   0.7435   0.7655
   0.750   0.0187   0.04039   0.02866   0.0078   0.7382   0.7699
   1.000   0.0299   0.04016   0.02840   0.0097   0.7343   0.7761
   1.250   0.0261   0.04051   0.02879   0.0136   0.7274   0.7812
   1.500   0.0401   0.04066   0.02897   0.0150   0.7224   0.7859
   1.750   0.0546   0.04043   0.02873   0.0164   0.7189   0.7922
   2.250   0.0664   0.04110   0.02950   0.0214   0.7066   0.8021
   2.500   0.0883   0.04098   0.02939   0.0217   0.7035   0.8079
   2.750   0.0782   0.04160   0.03008   0.0263   0.6949   0.8132
   3.000   0.0997   0.04171   0.03024   0.0266   0.6906   0.8186
   3.250   0.1074   0.04201   0.03059   0.0287   0.6849   0.8245
   3.500   0.1177   0.04243   0.03108   0.0304   0.6784   0.8298
   3.750   0.1418   0.04250   0.03121   0.0304   0.6746   0.8357
   4.000   0.1434   0.04312   0.03193   0.0331   0.6667   0.8416
   4.250   0.1652   0.04338   0.03228   0.0333   0.6616   0.8473
   4.500   0.1810   0.04370   0.03269   0.0342   0.6558   0.8536
   4.750   0.1939   0.04424   0.03333   0.0354   0.6483   0.8596
   5.000   0.2231   0.04432   0.03355   0.0349   0.6443   0.8659
   5.250   0.2276   0.04510   0.03445   0.0367   0.6347   0.8727
   5.500   0.2586   0.04521   0.03470   0.0360   0.6300   0.8790
   5.750   0.2662   0.04599   0.03562   0.0373   0.6203   0.8865
   6.000   0.3003   0.04607   0.03589   0.0362   0.6153   0.8929
   6.250   0.3112   0.04684   0.03682   0.0370   0.6046   0.9010
   6.500   0.3520   0.04673   0.03693   0.0353   0.5998   0.9073
   6.750   0.3660   0.04753   0.03792   0.0354   0.5880   0.9158
   7.000   0.3860   0.04810   0.03869   0.0351   0.5770   0.9251
   7.250   0.4355   0.04764   0.03855   0.0325   0.5708   0.9303
   7.500   0.4588   0.04806   0.03921   0.0318   0.5577   0.9401
   7.750   0.4919   0.04817   0.03961   0.0299   0.5441   0.9479
   8.000   0.5268   0.04778   0.03954   0.0286   0.5296   0.9571
   8.250   0.5692   0.04653   0.03862   0.0272   0.5137   0.9658
   8.500   0.5959   0.04624   0.03863   0.0262   0.4903   0.9781
   8.750   0.6332   0.04458   0.03730   0.0255   0.4651   0.9916
   9.000   0.6336   0.04398   0.03681   0.0289   0.4433   1.0000
   9.250   0.6303   0.04376   0.03660   0.0325   0.4182   1.0000
   9.500   0.6436   0.04275   0.03563   0.0352   0.3797   1.0000
   9.750   0.6689   0.04075   0.03320   0.0382   0.3027   1.0000
  10.000   0.6692   0.04175   0.03351   0.0408   0.2354   1.0000
  10.250   0.6624   0.04395   0.03524   0.0426   0.1906   1.0000
  10.500   0.6574   0.04633   0.03728   0.0439   0.1571   1.0000
  10.750   0.6550   0.04870   0.03936   0.0449   0.1327   1.0000
  11.000   0.6560   0.05093   0.04141   0.0457   0.1136   1.0000
  11.250   0.6600   0.05301   0.04335   0.0464   0.0995   1.0000
  11.500   0.6668   0.05494   0.04525   0.0471   0.0879   1.0000
  11.750   0.6762   0.05671   0.04695   0.0478   0.0791   1.0000
  12.000   0.6905   0.05818   0.04846   0.0486   0.0719   1.0000
  12.250   0.7071   0.05963   0.04998   0.0494   0.0653   1.0000
  12.500   0.7225   0.06120   0.05162   0.0499   0.0596   1.0000
  12.750   0.7509   0.06239   0.05292   0.0508   0.0550   1.0000
  13.000   0.7657   0.06454   0.05535   0.0512   0.0509   1.0000
  13.250   0.7762   0.06676   0.05769   0.0513   0.0480   1.0000
  13.500   0.7912   0.06914   0.06010   0.0516   0.0456   1.0000
  13.750   0.7929   0.07272   0.06405   0.0516   0.0446   1.0000
  14.000   0.7874   0.07682   0.06849   0.0512   0.0436   1.0000
  14.250   0.7773   0.08137   0.07332   0.0503   0.0429   1.0000
  14.500   0.7633   0.08648   0.07870   0.0489   0.0424   1.0000
  14.750   0.7477   0.09205   0.08449   0.0469   0.0425   1.0000
  15.000   0.7264   0.09871   0.09137   0.0439   0.0424   1.0000
  15.250   0.7025   0.10650   0.09936   0.0400   0.0427   1.0000
  15.500   0.6786   0.11517   0.10816   0.0352   0.0434   1.0000
<< Back to EPPLER E838 HYDROFOIL AIRFOIL (e838-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER E838 HYDROFOIL AIRFOIL (e838-il)