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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 50,000
Max Cl/Cd: 29.77 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e817-il-50000-n5.txt
Download as CSV file: xf-e817-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 817 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4950   0.10267   0.09580  -0.0510   1.0000   0.0298
 -10.500  -0.5055   0.09759   0.09080  -0.0521   1.0000   0.0295
 -10.250  -0.5199   0.09204   0.08533  -0.0535   1.0000   0.0292
 -10.000  -0.5330   0.08738   0.08072  -0.0545   1.0000   0.0283
  -9.750  -0.5520   0.08217   0.07554  -0.0559   1.0000   0.0279
  -9.500  -0.5723   0.07750   0.07089  -0.0569   1.0000   0.0274
  -9.250  -0.5944   0.07343   0.06682  -0.0573   1.0000   0.0270
  -9.000  -0.6194   0.06993   0.06331  -0.0569   1.0000   0.0267
  -8.750  -0.6448   0.06697   0.06032  -0.0558   1.0000   0.0264
  -8.500  -0.6632   0.06346   0.05670  -0.0557   1.0000   0.0261
  -8.250  -0.6766   0.05977   0.05279  -0.0554   1.0000   0.0261
  -8.000  -0.6837   0.05597   0.04871  -0.0550   1.0000   0.0262
  -7.750  -0.6843   0.05225   0.04464  -0.0547   1.0000   0.0265
  -7.500  -0.6791   0.04868   0.04065  -0.0544   1.0000   0.0272
  -7.250  -0.6688   0.04558   0.03711  -0.0539   1.0000   0.0288
  -7.000  -0.6542   0.04290   0.03377  -0.0536   1.0000   0.0319
  -6.750  -0.6403   0.04019   0.03104  -0.0530   1.0000   0.0349
  -6.500  -0.6230   0.03804   0.02865  -0.0520   1.0000   0.0382
  -6.250  -0.6045   0.03607   0.02636  -0.0506   1.0000   0.0416
  -6.000  -0.5865   0.03398   0.02415  -0.0497   1.0000   0.0475
  -5.750  -0.5665   0.03205   0.02213  -0.0499   1.0000   0.0618
  -5.500  -0.5437   0.02975   0.01971  -0.0504   1.0000   0.0802
  -5.250  -0.5168   0.02664   0.01720  -0.0533   1.0000   0.1450
  -5.000  -0.4902   0.02531   0.01658  -0.0550   1.0000   0.2967
  -4.750  -0.4667   0.02539   0.01657  -0.0546   1.0000   0.3575
  -4.500  -0.4444   0.02566   0.01654  -0.0537   1.0000   0.4013
  -4.250  -0.4234   0.02592   0.01669  -0.0523   1.0000   0.4326
  -4.000  -0.4011   0.02593   0.01650  -0.0514   1.0000   0.4552
  -3.750  -0.3780   0.02579   0.01614  -0.0508   1.0000   0.4714
  -3.500  -0.3547   0.02563   0.01577  -0.0503   1.0000   0.4856
  -3.250  -0.3310   0.02547   0.01541  -0.0499   1.0000   0.4992
  -3.000  -0.3074   0.02533   0.01510  -0.0495   1.0000   0.5127
  -2.750  -0.2838   0.02522   0.01483  -0.0491   1.0000   0.5263
  -2.500  -0.2604   0.02515   0.01461  -0.0488   1.0000   0.5399
  -2.250  -0.2369   0.02511   0.01436  -0.0484   1.0000   0.5539
  -2.000  -0.2137   0.02510   0.01424  -0.0480   1.0000   0.5681
  -1.750  -0.1874   0.02517   0.01421  -0.0482   0.9984   0.5830
  -1.500  -0.1576   0.02537   0.01432  -0.0490   0.9952   0.5991
  -1.250  -0.1279   0.02556   0.01443  -0.0499   0.9919   0.6159
  -1.000  -0.0991   0.02574   0.01449  -0.0506   0.9882   0.6331
  -0.750  -0.0703   0.02599   0.01473  -0.0512   0.9844   0.6500
  -0.500  -0.0399   0.02631   0.01503  -0.0522   0.9810   0.6683
  -0.250  -0.0132   0.02647   0.01519  -0.0525   0.9765   0.6871
   0.000   0.0146   0.02672   0.01545  -0.0529   0.9720   0.7058
   0.250   0.0448   0.02705   0.01580  -0.0538   0.9680   0.7270
   0.500   0.0686   0.02718   0.01600  -0.0534   0.9625   0.7468
   0.750   0.0969   0.02746   0.01635  -0.0538   0.9576   0.7697
   1.000   0.1218   0.02764   0.01662  -0.0536   0.9521   0.7942
   1.250   0.1466   0.02781   0.01691  -0.0533   0.9461   0.8210
   1.500   0.1709   0.02795   0.01717  -0.0528   0.9402   0.8525
   1.750   0.1960   0.02799   0.01736  -0.0526   0.9333   0.8958
   2.000   0.2293   0.02795   0.01746  -0.0546   0.9252   1.0000
   2.250   0.2678   0.02847   0.01802  -0.0579   0.9190   1.0000
   2.500   0.3017   0.02893   0.01851  -0.0602   0.9117   1.0000
   2.750   0.3395   0.02946   0.01909  -0.0630   0.9049   1.0000
   3.000   0.3703   0.02989   0.01960  -0.0644   0.8959   1.0000
   3.250   0.4070   0.03036   0.02018  -0.0668   0.8881   1.0000
   3.500   0.4413   0.03077   0.02081  -0.0685   0.8787   1.0000
   3.750   0.4724   0.03113   0.02134  -0.0697   0.8678   1.0000
   4.000   0.5052   0.03145   0.02186  -0.0709   0.8566   1.0000
   4.250   0.5393   0.03169   0.02233  -0.0722   0.8444   1.0000
   4.500   0.5737   0.03178   0.02270  -0.0733   0.8307   1.0000
   4.750   0.6106   0.03162   0.02297  -0.0744   0.8147   1.0000
   5.000   0.6473   0.03106   0.02278  -0.0748   0.7941   1.0000
   5.250   0.6833   0.02968   0.02180  -0.0738   0.7617   1.0000
   5.500   0.7094   0.02799   0.02044  -0.0706   0.7121   1.0000
   5.750   0.7399   0.02587   0.01858  -0.0670   0.6246   1.0000
   6.000   0.7805   0.02622   0.01643  -0.0641   0.2294   1.0000
   6.250   0.7866   0.02894   0.01817  -0.0616   0.1259   1.0000
   6.500   0.8027   0.03119   0.02008  -0.0601   0.0873   1.0000
   6.750   0.8245   0.03318   0.02194  -0.0594   0.0624   1.0000
   7.000   0.8645   0.03562   0.02469  -0.0604   0.0489   1.0000
   7.250   0.9061   0.03827   0.02742  -0.0624   0.0377   1.0000
   7.500   0.9506   0.04137   0.03107  -0.0639   0.0326   1.0000
   7.750   0.9838   0.04486   0.03498  -0.0643   0.0305   1.0000
   8.000   1.0071   0.04835   0.03889  -0.0635   0.0293   1.0000
   8.250   1.0227   0.05167   0.04255  -0.0621   0.0280   1.0000
   8.500   1.0323   0.05549   0.04662  -0.0605   0.0267   1.0000
   8.750   1.0360   0.05918   0.05073  -0.0578   0.0259   1.0000
   9.000   1.0358   0.06251   0.05455  -0.0547   0.0254   1.0000
   9.250   1.0311   0.06600   0.05846  -0.0515   0.0249   1.0000
   9.500   1.0213   0.06937   0.06218  -0.0481   0.0246   1.0000
   9.750   1.0086   0.07293   0.06602  -0.0450   0.0245   1.0000
  10.000   0.9936   0.07670   0.07005  -0.0426   0.0244   1.0000
  10.250   0.9772   0.08077   0.07434  -0.0410   0.0245   1.0000
  10.500   0.9600   0.08522   0.07898  -0.0403   0.0246   1.0000
  10.750   0.9422   0.09012   0.08405  -0.0406   0.0248   1.0000
  11.000   0.9245   0.09554   0.08960  -0.0420   0.0251   1.0000
  11.250   0.9080   0.10152   0.09567  -0.0445   0.0253   1.0000
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