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EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E852 AIRFOIL (e852-il)
Reynolds number: 50,000
Max Cl/Cd: 36.55 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e852-il-50000.txt
Download as CSV file: xf-e852-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E852 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4054   0.10973   0.10298  -0.0287   1.0000   0.2591
  -8.750  -0.4204   0.10874   0.10214  -0.0285   1.0000   0.2696
  -8.500  -0.4181   0.10585   0.09930  -0.0272   1.0000   0.2824
  -8.250  -0.4128   0.10258   0.09610  -0.0258   1.0000   0.2954
  -8.000  -0.4092   0.09957   0.09316  -0.0243   1.0000   0.3084
  -7.750  -0.4053   0.09652   0.09018  -0.0227   1.0000   0.3211
  -7.500  -0.4006   0.09332   0.08705  -0.0210   1.0000   0.3319
  -7.250  -0.4030   0.09072   0.08455  -0.0192   1.0000   0.3419
  -7.000  -0.4100   0.08854   0.08250  -0.0169   1.0000   0.3535
  -6.750  -0.4236   0.08704   0.08114  -0.0138   1.0000   0.3650
  -6.500  -0.4249   0.08454   0.07873  -0.0108   1.0000   0.3794
  -5.750  -0.5236   0.05772   0.05131  -0.0474   1.0000   0.1333
  -5.500  -0.5086   0.05177   0.04493  -0.0495   1.0000   0.1151
  -5.250  -0.4886   0.04655   0.03903  -0.0513   1.0000   0.1030
  -5.000  -0.4630   0.04209   0.03349  -0.0528   1.0000   0.0943
  -4.750  -0.4397   0.03851   0.02951  -0.0529   1.0000   0.0925
  -4.500  -0.4132   0.03536   0.02579  -0.0528   1.0000   0.0927
  -4.250  -0.3891   0.03295   0.02312  -0.0526   1.0000   0.1030
  -4.000  -0.3630   0.03058   0.02040  -0.0520   1.0000   0.1128
  -3.750  -0.3377   0.02847   0.01810  -0.0506   1.0000   0.1244
  -3.500  -0.3149   0.02666   0.01642  -0.0496   1.0000   0.1588
  -3.250  -0.2894   0.02425   0.01443  -0.0488   1.0000   0.2193
  -3.000  -0.2833   0.02283   0.01547  -0.0416   1.0000   0.6232
  -2.750  -0.2848   0.02344   0.01612  -0.0330   1.0000   0.7010
  -2.500  -0.2855   0.02365   0.01631  -0.0253   1.0000   0.7547
  -2.250  -0.2861   0.02357   0.01617  -0.0178   1.0000   0.8003
  -2.000  -0.2870   0.02329   0.01571  -0.0108   1.0000   0.8478
  -1.750  -0.2861   0.02283   0.01522  -0.0038   1.0000   0.9022
  -1.500  -0.2016   0.02315   0.01497  -0.0135   1.0000   0.9789
  -1.250  -0.1669   0.02273   0.01424  -0.0181   1.0000   1.0000
  -1.000  -0.1603   0.02211   0.01345  -0.0177   1.0000   1.0000
  -0.750  -0.1360   0.02196   0.01301  -0.0202   1.0000   1.0000
  -0.500  -0.1057   0.02207   0.01274  -0.0235   1.0000   1.0000
  -0.250  -0.0747   0.02234   0.01271  -0.0264   1.0000   1.0000
   0.000  -0.0451   0.02269   0.01280  -0.0289   1.0000   1.0000
   0.250  -0.0172   0.02311   0.01297  -0.0307   1.0000   1.0000
   0.500   0.0091   0.02356   0.01321  -0.0320   1.0000   1.0000
   0.750   0.0339   0.02406   0.01348  -0.0330   1.0000   1.0000
   1.000   0.0579   0.02459   0.01385  -0.0338   1.0000   1.0000
   1.250   0.0810   0.02515   0.01428  -0.0344   1.0000   1.0000
   1.500   0.1035   0.02574   0.01477  -0.0348   1.0000   1.0000
   1.750   0.1255   0.02637   0.01532  -0.0352   1.0000   1.0000
   2.000   0.1469   0.02704   0.01593  -0.0355   1.0000   1.0000
   2.250   0.1679   0.02774   0.01658  -0.0358   1.0000   1.0000
   2.500   0.1885   0.02848   0.01729  -0.0360   1.0000   1.0000
   2.750   0.2086   0.02926   0.01807  -0.0362   1.0000   1.0000
   3.000   0.2284   0.03009   0.01890  -0.0363   1.0000   1.0000
   3.250   0.2476   0.03096   0.01981  -0.0365   1.0000   1.0000
   3.500   0.2664   0.03189   0.02082  -0.0367   1.0000   1.0000
   3.750   0.2848   0.03288   0.02186  -0.0369   1.0000   1.0000
   4.000   0.3027   0.03394   0.02299  -0.0371   1.0000   1.0000
   4.250   0.3464   0.03591   0.02512  -0.0424   0.9851   1.0000
   4.500   0.3977   0.03788   0.02731  -0.0487   0.9621   1.0000
   4.750   0.4456   0.03955   0.02930  -0.0539   0.9391   1.0000
   5.000   0.4940   0.04103   0.03106  -0.0588   0.9147   1.0000
   5.250   0.5412   0.04221   0.03257  -0.0629   0.8881   1.0000
   5.500   0.5885   0.04303   0.03377  -0.0663   0.8580   1.0000
   5.750   0.6528   0.04298   0.03438  -0.0706   0.8211   1.0000
   6.000   0.7467   0.03968   0.03196  -0.0744   0.7671   1.0000
   6.250   0.8830   0.02416   0.01630  -0.0623   0.3800   1.0000
   6.500   0.8697   0.02798   0.01831  -0.0560   0.2373   1.0000
   6.750   0.9055   0.03206   0.02170  -0.0560   0.1519   1.0000
   7.000   0.9663   0.03677   0.02616  -0.0593   0.1077   1.0000
   7.250   0.9960   0.04044   0.02995  -0.0592   0.0883   1.0000
   7.500   1.0256   0.04453   0.03458  -0.0582   0.0830   1.0000
   7.750   1.0513   0.04921   0.03942  -0.0576   0.0792   1.0000
   8.000   1.0614   0.05299   0.04381  -0.0548   0.0766   1.0000
   8.250   1.0673   0.05655   0.04799  -0.0516   0.0748   1.0000
   8.500   1.0705   0.06048   0.05242  -0.0487   0.0740   1.0000
   8.750   1.0720   0.06480   0.05715  -0.0460   0.0750   1.0000
   9.000   1.0748   0.06973   0.06234  -0.0439   0.0769   1.0000
   9.250   1.0672   0.07378   0.06688  -0.0408   0.0806   1.0000
   9.500   1.0416   0.07795   0.07151  -0.0373   0.0842   1.0000
   9.750   1.0243   0.08227   0.07602  -0.0348   0.0869   1.0000
  10.000   1.0244   0.08770   0.08157  -0.0339   0.0926   1.0000
  10.250   0.9878   0.09147   0.08554  -0.0326   0.0937   1.0000
  10.500   0.9494   0.09718   0.09139  -0.0346   0.0964   1.0000
  10.750   0.9259   0.10511   0.09941  -0.0387   0.1074   1.0000
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