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EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 857 AIRFOIL (e857-il)
Reynolds number: 100,000
Max Cl/Cd: 41.23 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e857-il-100000-n5.txt
Download as CSV file: xf-e857-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 857 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.4338   0.10409   0.09871  -0.0647   1.0000   0.0299
 -13.750  -0.5044   0.08741   0.08169  -0.0737   1.0000   0.0291
 -13.500  -0.5342   0.08007   0.07416  -0.0770   1.0000   0.0291
 -13.250  -0.5557   0.07469   0.06864  -0.0788   1.0000   0.0290
 -13.000  -0.5733   0.07032   0.06415  -0.0799   1.0000   0.0292
 -12.750  -0.5902   0.06641   0.06013  -0.0804   1.0000   0.0296
 -12.500  -0.6062   0.06294   0.05655  -0.0804   1.0000   0.0301
 -12.250  -0.6202   0.06003   0.05354  -0.0798   1.0000   0.0304
 -12.000  -0.6302   0.05720   0.05058  -0.0796   0.9992   0.0308
 -11.750  -0.6127   0.05399   0.04723  -0.0841   0.9935   0.0317
 -11.500  -0.5941   0.05127   0.04446  -0.0879   0.9866   0.0329
 -11.250  -0.5760   0.04860   0.04165  -0.0913   0.9791   0.0342
 -11.000  -0.5596   0.04601   0.03889  -0.0941   0.9696   0.0360
 -10.750  -0.5460   0.04383   0.03670  -0.0961   0.9571   0.0374
 -10.500  -0.5338   0.04166   0.03440  -0.0976   0.9432   0.0396
 -10.250  -0.5206   0.03963   0.03233  -0.0989   0.9296   0.0416
 -10.000  -0.5073   0.03768   0.03032  -0.1002   0.9163   0.0440
  -9.750  -0.4931   0.03578   0.02831  -0.1013   0.9039   0.0469
  -9.500  -0.4780   0.03403   0.02650  -0.1023   0.8907   0.0502
  -9.250  -0.4604   0.03244   0.02484  -0.1029   0.8768   0.0540
  -9.000  -0.4378   0.03092   0.02323  -0.1041   0.8643   0.0595
  -8.750  -0.4074   0.02940   0.02161  -0.1065   0.8544   0.0664
  -8.500  -0.3833   0.02813   0.02029  -0.1076   0.8404   0.0738
  -8.250  -0.3544   0.02691   0.01899  -0.1094   0.8274   0.0829
  -8.000  -0.3193   0.02570   0.01768  -0.1123   0.8159   0.0949
  -7.750  -0.2919   0.02463   0.01655  -0.1136   0.8017   0.1071
  -7.500  -0.2664   0.02363   0.01551  -0.1145   0.7874   0.1209
  -7.250  -0.2395   0.02266   0.01451  -0.1156   0.7739   0.1380
  -7.000  -0.2113   0.02176   0.01357  -0.1168   0.7610   0.1612
  -6.750  -0.1904   0.02095   0.01281  -0.1166   0.7471   0.1879
  -6.500  -0.1667   0.02019   0.01215  -0.1167   0.7345   0.2259
  -6.250  -0.1394   0.01970   0.01178  -0.1173   0.7228   0.2738
  -6.000  -0.1153   0.01955   0.01166  -0.1168   0.7103   0.3122
  -5.750  -0.0868   0.01958   0.01158  -0.1169   0.6992   0.3419
  -5.500  -0.0597   0.01963   0.01147  -0.1167   0.6878   0.3651
  -5.250  -0.0331   0.01973   0.01142  -0.1164   0.6771   0.3830
  -5.000  -0.0050   0.01987   0.01140  -0.1162   0.6672   0.3972
  -4.750   0.0207   0.01995   0.01134  -0.1157   0.6573   0.4092
  -4.500   0.0483   0.02001   0.01118  -0.1157   0.6482   0.4211
  -4.250   0.0736   0.02014   0.01124  -0.1150   0.6387   0.4304
  -4.000   0.1001   0.02023   0.01112  -0.1147   0.6300   0.4432
  -3.750   0.1259   0.02045   0.01130  -0.1140   0.6215   0.4528
  -3.500   0.1514   0.02048   0.01115  -0.1136   0.6133   0.4632
  -3.250   0.1790   0.02059   0.01118  -0.1133   0.6064   0.4699
  -3.000   0.2033   0.02060   0.01107  -0.1127   0.5984   0.4781
  -2.750   0.2302   0.02059   0.01092  -0.1126   0.5915   0.4844
  -2.500   0.2557   0.02062   0.01088  -0.1121   0.5845   0.4895
  -2.250   0.2807   0.02062   0.01077  -0.1116   0.5772   0.4955
  -2.000   0.3087   0.02058   0.01051  -0.1119   0.5714   0.5018
  -1.750   0.3332   0.02061   0.01053  -0.1112   0.5650   0.5057
  -1.500   0.3585   0.02065   0.01051  -0.1108   0.5588   0.5106
  -1.250   0.3859   0.02068   0.01039  -0.1108   0.5536   0.5163
  -1.000   0.4119   0.02071   0.01029  -0.1107   0.5481   0.5218
  -0.750   0.4359   0.02076   0.01035  -0.1100   0.5420   0.5257
  -0.500   0.4620   0.02082   0.01034  -0.1097   0.5368   0.5308
  -0.250   0.4901   0.02090   0.01028  -0.1099   0.5324   0.5366
   0.000   0.5135   0.02099   0.01034  -0.1093   0.5270   0.5420
   0.250   0.5382   0.02109   0.01045  -0.1087   0.5222   0.5462
   0.500   0.5646   0.02119   0.01049  -0.1086   0.5180   0.5517
   0.750   0.5932   0.02131   0.01048  -0.1089   0.5142   0.5581
   1.000   0.6150   0.02146   0.01067  -0.1079   0.5092   0.5633
   1.250   0.6385   0.02159   0.01083  -0.1072   0.5045   0.5683
   1.500   0.6643   0.02173   0.01092  -0.1070   0.5005   0.5745
   1.750   0.6927   0.02189   0.01097  -0.1073   0.4972   0.5815
   2.000   0.7162   0.02209   0.01123  -0.1066   0.4935   0.5871
   2.250   0.7378   0.02231   0.01150  -0.1057   0.4894   0.5936
   2.500   0.7618   0.02252   0.01169  -0.1052   0.4854   0.6008
   2.750   0.7868   0.02268   0.01187  -0.1048   0.4819   0.6072
   3.000   0.8145   0.02286   0.01199  -0.1049   0.4788   0.6156
   3.250   0.8358   0.02313   0.01232  -0.1040   0.4753   0.6233
   3.500   0.8552   0.02342   0.01272  -0.1026   0.4716   0.6313
   3.750   0.8776   0.02372   0.01304  -0.1019   0.4683   0.6404
   4.000   0.9014   0.02396   0.01332  -0.1014   0.4651   0.6495
   4.250   0.9281   0.02418   0.01353  -0.1014   0.4623   0.6607
   4.500   0.9563   0.02441   0.01375  -0.1016   0.4597   0.6724
   4.750   0.9694   0.02482   0.01434  -0.0993   0.4559   0.6840
   5.000   0.9865   0.02521   0.01483  -0.0977   0.4525   0.6979
   5.250   1.0062   0.02554   0.01528  -0.0965   0.4495   0.7134
   5.500   1.0282   0.02582   0.01564  -0.0957   0.4468   0.7324
   5.750   1.0527   0.02604   0.01592  -0.0953   0.4443   0.7557
   6.000   1.0801   0.02620   0.01614  -0.0952   0.4421   0.7858
   6.500   1.0995   0.02702   0.01752  -0.0896   0.4351   1.0000
   6.750   1.1151   0.02762   0.01814  -0.0881   0.4322   1.0000
   7.000   1.1350   0.02814   0.01865  -0.0873   0.4296   1.0000
   7.250   1.1600   0.02856   0.01902  -0.0873   0.4272   1.0000
   7.500   1.1903   0.02891   0.01931  -0.0881   0.4250   1.0000
   7.750   1.1968   0.02973   0.02021  -0.0852   0.4221   1.0000
   8.000   1.1923   0.03084   0.02146  -0.0808   0.4185   1.0000
   8.250   1.1971   0.03182   0.02252  -0.0780   0.4154   1.0000
   8.500   1.2088   0.03264   0.02339  -0.0762   0.4127   1.0000
   8.750   1.2287   0.03321   0.02397  -0.0755   0.4103   1.0000
   9.000   1.2577   0.03350   0.02423  -0.0760   0.4082   1.0000
   9.250   1.2767   0.03416   0.02491  -0.0753   0.4058   1.0000
   9.500   1.2276   0.03731   0.02835  -0.0667   0.4008   1.0000
   9.750   1.2069   0.03989   0.03107  -0.0624   0.3967   1.0000
  10.000   1.2137   0.04122   0.03246  -0.0608   0.3938   1.0000
  10.250   1.2386   0.04156   0.03280  -0.0608   0.3918   1.0000
  10.500   1.2767   0.04122   0.03245  -0.0618   0.3901   1.0000
  10.750   1.0506   0.06191   0.05358  -0.0511   0.3703   1.0000
  11.000   1.0989   0.05942   0.05109  -0.0510   0.3711   1.0000
  11.250   1.1513   0.05675   0.04841  -0.0513   0.3719   1.0000
  13.250   0.9289   0.10932   0.10163  -0.0551   0.2975   1.0000
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