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EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E850 AIRFOIL (e850-il)
Reynolds number: 50,000
Max Cl/Cd: 26.7 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e850-il-50000-n5.txt
Download as CSV file: xf-e850-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E850 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5074   0.09583   0.08870  -0.0347   1.0000   0.0210
  -8.750  -0.5108   0.09171   0.08466  -0.0359   1.0000   0.0209
  -8.500  -0.5142   0.08796   0.08098  -0.0367   1.0000   0.0204
  -8.250  -0.5199   0.08383   0.07693  -0.0381   1.0000   0.0202
  -8.000  -0.5287   0.07980   0.07297  -0.0393   1.0000   0.0199
  -7.750  -0.5396   0.07601   0.06925  -0.0405   1.0000   0.0197
  -7.500  -0.5480   0.07206   0.06531  -0.0416   1.0000   0.0194
  -7.250  -0.5552   0.06813   0.06133  -0.0422   1.0000   0.0192
  -7.000  -0.5595   0.06427   0.05737  -0.0426   1.0000   0.0190
  -6.750  -0.5608   0.06038   0.05331  -0.0428   1.0000   0.0187
  -6.500  -0.5589   0.05636   0.04907  -0.0428   1.0000   0.0187
  -6.250  -0.5529   0.05247   0.04488  -0.0428   1.0000   0.0186
  -6.000  -0.5431   0.04869   0.04073  -0.0426   1.0000   0.0186
  -5.750  -0.5298   0.04502   0.03662  -0.0424   1.0000   0.0191
  -5.500  -0.5129   0.04163   0.03271  -0.0420   1.0000   0.0201
  -5.250  -0.4933   0.03871   0.02923  -0.0413   1.0000   0.0211
  -5.000  -0.4723   0.03586   0.02587  -0.0407   1.0000   0.0226
  -4.750  -0.4524   0.03294   0.02244  -0.0403   1.0000   0.0255
  -4.500  -0.4297   0.03077   0.01995  -0.0393   1.0000   0.0278
  -4.250  -0.4066   0.02881   0.01768  -0.0378   1.0000   0.0291
  -4.000  -0.3843   0.02709   0.01568  -0.0360   1.0000   0.0311
  -3.750  -0.3620   0.02558   0.01383  -0.0343   1.0000   0.0343
  -3.500  -0.3394   0.02409   0.01223  -0.0336   1.0000   0.0473
  -3.250  -0.3133   0.02167   0.01016  -0.0343   1.0000   0.1052
  -3.000  -0.3015   0.01911   0.01021  -0.0311   1.0000   0.6084
  -2.750  -0.2941   0.01928   0.01050  -0.0247   1.0000   0.6963
  -2.500  -0.2826   0.01925   0.01034  -0.0200   1.0000   0.7452
  -2.250  -0.2642   0.01905   0.00990  -0.0177   1.0000   0.7717
  -2.000  -0.2431   0.01881   0.00940  -0.0162   1.0000   0.7910
  -1.750  -0.2212   0.01858   0.00876  -0.0151   1.0000   0.8112
  -1.500  -0.1998   0.01836   0.00838  -0.0139   1.0000   0.8323
  -1.250  -0.1777   0.01814   0.00803  -0.0129   1.0000   0.8564
  -1.000  -0.1526   0.01794   0.00773  -0.0126   1.0000   0.8862
  -0.750  -0.1185   0.01777   0.00745  -0.0144   1.0000   0.9274
  -0.500  -0.0840   0.01751   0.00706  -0.0169   1.0000   1.0000
  -0.250  -0.0569   0.01757   0.00683  -0.0181   1.0000   1.0000
   0.000  -0.0303   0.01768   0.00676  -0.0190   1.0000   1.0000
   0.250  -0.0044   0.01783   0.00676  -0.0196   1.0000   1.0000
   0.500   0.0209   0.01802   0.00683  -0.0200   1.0000   1.0000
   0.750   0.0457   0.01824   0.00697  -0.0203   1.0000   1.0000
   1.000   0.0699   0.01848   0.00715  -0.0205   1.0000   1.0000
   1.250   0.0938   0.01875   0.00740  -0.0206   1.0000   1.0000
   1.500   0.1172   0.01904   0.00770  -0.0205   1.0000   1.0000
   1.750   0.1403   0.01937   0.00803  -0.0205   1.0000   1.0000
   2.000   0.1630   0.01972   0.00843  -0.0204   1.0000   1.0000
   2.250   0.1854   0.02011   0.00888  -0.0203   1.0000   1.0000
   2.500   0.2222   0.02076   0.00967  -0.0231   0.9925   1.0000
   2.750   0.2622   0.02142   0.01053  -0.0264   0.9827   1.0000
   3.000   0.3023   0.02201   0.01159  -0.0296   0.9715   1.0000
   3.250   0.3440   0.02256   0.01248  -0.0330   0.9587   1.0000
   3.500   0.3893   0.02302   0.01336  -0.0368   0.9439   1.0000
   3.750   0.4354   0.02318   0.01401  -0.0402   0.9222   1.0000
   4.000   0.5127   0.02156   0.01325  -0.0458   0.8580   1.0000
   4.250   0.5847   0.02190   0.01076  -0.0456   0.1498   1.0000
   4.500   0.6053   0.02439   0.01271  -0.0445   0.0802   1.0000
   4.750   0.6321   0.02642   0.01484  -0.0439   0.0583   1.0000
   5.000   0.6641   0.02849   0.01708  -0.0441   0.0428   1.0000
   5.250   0.7012   0.03164   0.02035  -0.0448   0.0375   1.0000
   5.500   0.7348   0.03462   0.02384  -0.0445   0.0349   1.0000
   5.750   0.7593   0.03710   0.02669  -0.0436   0.0296   1.0000
   6.000   0.7786   0.04038   0.03025  -0.0426   0.0260   1.0000
   6.250   0.7984   0.04362   0.03410  -0.0407   0.0250   1.0000
   6.500   0.8140   0.04728   0.03829  -0.0386   0.0247   1.0000
   6.750   0.8259   0.05104   0.04254  -0.0364   0.0246   1.0000
   7.000   0.8347   0.05492   0.04685  -0.0342   0.0246   1.0000
   7.250   0.8405   0.05888   0.05120  -0.0320   0.0246   1.0000
   7.500   0.8432   0.06295   0.05560  -0.0299   0.0247   1.0000
   7.750   0.8430   0.06704   0.05998  -0.0281   0.0248   1.0000
   8.000   0.8399   0.07117   0.06434  -0.0264   0.0250   1.0000
   8.250   0.8347   0.07518   0.06854  -0.0250   0.0252   1.0000
   8.500   0.8263   0.07918   0.07267  -0.0238   0.0254   1.0000
   8.750   0.8153   0.08305   0.07663  -0.0226   0.0256   1.0000
   9.000   0.8045   0.08717   0.08081  -0.0224   0.0258   1.0000
   9.250   0.7942   0.09162   0.08530  -0.0232   0.0261   1.0000
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