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EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 378 AIRFOIL (e378-il)
Reynolds number: 100,000
Max Cl/Cd: 65.11 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e378-il-100000-n5.txt
Download as CSV file: xf-e378-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 378 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2747   0.11517   0.11081  -0.0034   1.0000   0.0204
  -8.000  -0.2660   0.11321   0.10892  -0.0052   1.0000   0.0204
  -7.750  -0.2577   0.11134   0.10714  -0.0070   1.0000   0.0205
  -7.500  -0.2447   0.10911   0.10500  -0.0100   0.9578   0.0205
  -7.250  -0.2266   0.10197   0.09785  -0.0110   0.9220   0.0209
  -7.000  -0.2086   0.09733   0.09309  -0.0129   0.8714   0.0214
  -6.750  -0.1968   0.09445   0.09012  -0.0141   0.8399   0.0219
  -6.500  -0.1859   0.09207   0.08761  -0.0149   0.8100   0.0223
  -6.250  -0.1732   0.08961   0.08508  -0.0165   0.7952   0.0229
  -6.000  -0.1590   0.08713   0.08255  -0.0187   0.7843   0.0235
  -5.750  -0.1451   0.08483   0.08013  -0.0201   0.7648   0.0242
  -5.500  -0.1284   0.08232   0.07757  -0.0227   0.7509   0.0251
  -5.250  -0.1083   0.07996   0.07520  -0.0262   0.7391   0.0269
  -5.000  -0.0733   0.07968   0.07488  -0.0351   0.7281   0.0285
  -4.750  -0.0394   0.07873   0.07382  -0.0428   0.7173   0.0288
  -4.500  -0.0340   0.07285   0.06795  -0.0402   0.7102   0.0294
  -4.250  -0.0197   0.06912   0.06419  -0.0404   0.7036   0.0304
  -4.000   0.0007   0.06640   0.06137  -0.0423   0.6952   0.0315
  -3.750   0.0246   0.06378   0.05865  -0.0450   0.6870   0.0332
  -3.500   0.0518   0.06125   0.05601  -0.0485   0.6782   0.0353
  -3.250   0.0872   0.05911   0.05370  -0.0539   0.6700   0.0382
  -3.000   0.1415   0.05816   0.05256  -0.0637   0.6614   0.0395
  -2.750   0.1814   0.05595   0.05015  -0.0692   0.6544   0.0397
  -2.500   0.2014   0.05156   0.04579  -0.0703   0.6473   0.0404
  -2.250   0.2218   0.04822   0.04240  -0.0710   0.6412   0.0415
  -2.000   0.2526   0.04563   0.03974  -0.0737   0.6339   0.0426
  -1.750   0.2857   0.04328   0.03725  -0.0767   0.6279   0.0445
  -1.500   0.3437   0.04258   0.03621  -0.0841   0.6210   0.0521
  -1.250   0.3814   0.04016   0.03360  -0.0873   0.6150   0.0523
  -1.000   0.4024   0.03576   0.02914  -0.0877   0.6100   0.0363
  -0.750   0.4409   0.03326   0.02646  -0.0907   0.6036   0.0339
  -0.500   0.4795   0.03089   0.02381  -0.0934   0.5986   0.0334
  -0.250   0.5207   0.02863   0.02124  -0.0962   0.5927   0.0385
   0.000   0.5610   0.02578   0.01798  -0.0984   0.5874   0.0398
   0.250   0.5878   0.02516   0.01721  -0.0986   0.5823   0.0457
   0.500   0.6253   0.02273   0.01432  -0.1001   0.5765   0.0504
   0.750   0.6595   0.02049   0.01149  -0.1010   0.5717   0.0538
   1.000   0.6884   0.01992   0.01065  -0.1010   0.5665   0.0631
   1.250   0.7177   0.01925   0.00976  -0.1011   0.5606   0.0711
   1.500   0.7457   0.01885   0.00911  -0.1008   0.5559   0.0834
   1.750   0.7735   0.01862   0.00872  -0.1007   0.5504   0.0963
   2.000   0.8019   0.01850   0.00847  -0.1007   0.5448   0.1094
   2.250   0.8313   0.01833   0.00805  -0.1006   0.5405   0.1200
   2.500   0.8594   0.01836   0.00807  -0.1007   0.5344   0.1332
   2.750   0.8872   0.01830   0.00798  -0.1005   0.5292   0.1425
   3.000   0.9144   0.01830   0.00791  -0.1002   0.5245   0.1535
   3.250   0.9413   0.01841   0.00806  -0.1000   0.5186   0.1700
   3.500   0.9679   0.01848   0.00809  -0.0997   0.5138   0.1854
   3.750   0.9944   0.01862   0.00828  -0.0994   0.5085   0.2036
   4.000   1.0209   0.01878   0.00854  -0.0991   0.5028   0.2247
   4.250   1.0472   0.01891   0.00867  -0.0988   0.4983   0.2488
   4.500   1.0735   0.01912   0.00901  -0.0986   0.4921   0.2782
   4.750   1.0996   0.01926   0.00926  -0.0983   0.4866   0.3192
   5.000   1.1300   0.01874   0.00947  -0.0990   0.4811   1.0000
   5.250   1.1559   0.01907   0.00987  -0.0986   0.4742   1.0000
   5.500   1.1817   0.01929   0.01001  -0.0981   0.4690   1.0000
   5.750   1.2071   0.01963   0.01049  -0.0978   0.4608   1.0000
   6.000   1.2327   0.01983   0.01065  -0.0972   0.4547   1.0000
   6.250   1.2577   0.02016   0.01122  -0.0968   0.4458   1.0000
   6.500   1.2829   0.02040   0.01151  -0.0962   0.4382   1.0000
   6.750   1.3077   0.02064   0.01186  -0.0957   0.4290   1.0000
   7.000   1.3322   0.02092   0.01229  -0.0952   0.4190   1.0000
   7.250   1.3567   0.02114   0.01262  -0.0946   0.4088   1.0000
   7.500   1.3809   0.02136   0.01300  -0.0939   0.3978   1.0000
   7.750   1.4046   0.02162   0.01341  -0.0933   0.3848   1.0000
   8.000   1.4279   0.02193   0.01389  -0.0926   0.3700   1.0000
   8.250   1.4506   0.02231   0.01446  -0.0920   0.3528   1.0000
   8.500   1.4726   0.02273   0.01503  -0.0912   0.3329   1.0000
   8.750   1.4934   0.02327   0.01567  -0.0904   0.3088   1.0000
   9.000   1.5124   0.02400   0.01651  -0.0895   0.2783   1.0000
   9.250   1.5287   0.02507   0.01751  -0.0884   0.2431   1.0000
   9.500   1.5413   0.02654   0.01888  -0.0872   0.2072   1.0000
   9.750   1.5508   0.02832   0.02055  -0.0859   0.1761   1.0000
  10.000   1.5575   0.03027   0.02245  -0.0844   0.1507   1.0000
  10.250   1.5624   0.03225   0.02446  -0.0828   0.1303   1.0000
  10.500   1.5624   0.03449   0.02670  -0.0810   0.1140   1.0000
  10.750   1.5570   0.03691   0.02916  -0.0790   0.1020   1.0000
  11.000   1.5510   0.03973   0.03205  -0.0778   0.0917   1.0000
  11.250   1.5440   0.04299   0.03536  -0.0771   0.0837   1.0000
  11.500   1.5377   0.04642   0.03886  -0.0768   0.0757   1.0000
  11.750   1.5317   0.05003   0.04264  -0.0768   0.0683   1.0000
  12.000   1.5238   0.05400   0.04666  -0.0770   0.0628   1.0000
  12.250   1.5183   0.05778   0.05057  -0.0771   0.0566   1.0000
  12.500   1.5100   0.06201   0.05488  -0.0776   0.0520   1.0000
  12.750   1.5030   0.06611   0.05908  -0.0778   0.0477   1.0000
  13.000   1.4964   0.07028   0.06341  -0.0783   0.0440   1.0000
  13.250   1.4871   0.07487   0.06807  -0.0790   0.0410   1.0000
  13.500   1.4797   0.07926   0.07257  -0.0795   0.0377   1.0000
  13.750   1.4736   0.08371   0.07719  -0.0804   0.0340   1.0000
  14.000   1.4650   0.08870   0.08227  -0.0817   0.0314   1.0000
  14.250   1.4570   0.09353   0.08715  -0.0826   0.0292   1.0000
  14.500   1.4526   0.09804   0.09190  -0.0836   0.0265   1.0000
  14.750   1.4455   0.10324   0.09725  -0.0853   0.0241   1.0000
  15.000   1.4364   0.10895   0.10305  -0.0876   0.0222   1.0000
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