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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 200,000
Max Cl/Cd: 82.5 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e853-il-200000-n5.txt
Download as CSV file: xf-e853-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4227   0.08768   0.08422  -0.0477   1.0000   0.0075
  -9.500  -0.4320   0.08257   0.07918  -0.0492   1.0000   0.0075
  -9.250  -0.4418   0.07766   0.07434  -0.0507   1.0000   0.0073
  -9.000  -0.4593   0.07064   0.06740  -0.0532   1.0000   0.0073
  -8.750  -0.4804   0.06379   0.06058  -0.0560   1.0000   0.0071
  -8.500  -0.4906   0.05572   0.05239  -0.0662   0.9935   0.0069
  -8.250  -0.4874   0.04673   0.04301  -0.0790   0.9806   0.0068
  -8.000  -0.4786   0.03980   0.03557  -0.0851   0.9698   0.0067
  -7.500  -0.4473   0.03019   0.02486  -0.0896   0.9496   0.0067
  -7.250  -0.4202   0.02667   0.02080  -0.0916   0.9445   0.0068
  -7.000  -0.3960   0.02413   0.01784  -0.0921   0.9361   0.0070
  -6.750  -0.3648   0.02191   0.01526  -0.0936   0.9317   0.0074
  -6.500  -0.3366   0.02027   0.01336  -0.0943   0.9243   0.0078
  -6.250  -0.3044   0.01849   0.01140  -0.0960   0.9193   0.0089
  -6.000  -0.2714   0.01778   0.01061  -0.0977   0.9130   0.0110
  -5.750  -0.2374   0.01687   0.00950  -0.0994   0.9068   0.0131
  -5.500  -0.2045   0.01547   0.00797  -0.1011   0.9002   0.0163
  -5.250  -0.1704   0.01460   0.00699  -0.1028   0.8931   0.0243
  -5.000  -0.1368   0.01384   0.00620  -0.1045   0.8855   0.0396
  -4.750  -0.1026   0.01318   0.00556  -0.1063   0.8779   0.0639
  -4.500  -0.0708   0.01254   0.00501  -0.1076   0.8692   0.1029
  -4.250  -0.0381   0.01183   0.00445  -0.1093   0.8615   0.1701
  -4.000  -0.0088   0.01101   0.00404  -0.1105   0.8523   0.2918
  -3.750   0.0206   0.01059   0.00395  -0.1112   0.8436   0.4067
  -3.500   0.0512   0.01052   0.00385  -0.1118   0.8357   0.4551
  -3.250   0.0799   0.01051   0.00376  -0.1119   0.8271   0.4798
  -3.000   0.1096   0.01050   0.00363  -0.1123   0.8195   0.4989
  -2.750   0.1378   0.01051   0.00358  -0.1123   0.8114   0.5176
  -2.500   0.1664   0.01055   0.00355  -0.1124   0.8042   0.5388
  -2.250   0.1946   0.01057   0.00350  -0.1125   0.7969   0.5535
  -2.000   0.2226   0.01057   0.00344  -0.1125   0.7901   0.5623
  -1.750   0.2508   0.01057   0.00336  -0.1126   0.7833   0.5700
  -1.500   0.2790   0.01058   0.00331  -0.1127   0.7772   0.5772
  -1.250   0.3069   0.01058   0.00327  -0.1127   0.7707   0.5841
  -1.000   0.3352   0.01060   0.00322  -0.1129   0.7651   0.5911
  -0.750   0.3627   0.01062   0.00323  -0.1128   0.7587   0.5981
  -0.500   0.3909   0.01064   0.00322  -0.1129   0.7536   0.6054
  -0.250   0.4184   0.01067   0.00325  -0.1129   0.7477   0.6126
   0.000   0.4461   0.01070   0.00327  -0.1130   0.7422   0.6204
   0.250   0.4741   0.01074   0.00331  -0.1130   0.7374   0.6279
   0.500   0.5013   0.01078   0.00338  -0.1130   0.7316   0.6365
   0.750   0.5290   0.01082   0.00345  -0.1130   0.7267   0.6446
   1.000   0.5565   0.01088   0.00354  -0.1130   0.7218   0.6536
   1.250   0.5836   0.01093   0.00364  -0.1129   0.7164   0.6632
   1.500   0.6114   0.01098   0.00373  -0.1129   0.7119   0.6730
   1.750   0.6381   0.01104   0.00390  -0.1127   0.7066   0.6837
   2.000   0.6651   0.01110   0.00404  -0.1126   0.7013   0.6953
   2.250   0.6926   0.01117   0.00416  -0.1126   0.6968   0.7078
   2.500   0.7183   0.01123   0.00434  -0.1122   0.6904   0.7214
   2.750   0.7450   0.01128   0.00450  -0.1119   0.6844   0.7360
   3.000   0.7700   0.01132   0.00467  -0.1113   0.6762   0.7521
   3.250   0.7955   0.01136   0.00480  -0.1107   0.6681   0.7705
   3.500   0.8195   0.01138   0.00492  -0.1097   0.6573   0.7913
   3.750   0.8423   0.01138   0.00506  -0.1085   0.6439   0.8154
   4.250   0.8833   0.01131   0.00522  -0.1049   0.6110   0.8891
   4.500   0.9100   0.01127   0.00530  -0.1045   0.5937   1.0000
   4.750   0.9345   0.01142   0.00546  -0.1038   0.5741   1.0000
   5.000   0.9578   0.01161   0.00564  -0.1029   0.5473   1.0000
   5.250   0.9789   0.01188   0.00587  -0.1016   0.5074   1.0000
   5.500   0.9943   0.01243   0.00613  -0.0992   0.4380   1.0000
   5.750   1.0014   0.01354   0.00669  -0.0956   0.3409   1.0000
   6.000   1.0089   0.01479   0.00747  -0.0925   0.2551   1.0000
   6.250   1.0188   0.01596   0.00826  -0.0898   0.1863   1.0000
   6.500   1.0316   0.01695   0.00902  -0.0876   0.1390   1.0000
   6.750   1.0454   0.01786   0.00977  -0.0855   0.1057   1.0000
   7.000   1.0588   0.01875   0.01054  -0.0834   0.0796   1.0000
   7.250   1.0717   0.01959   0.01136  -0.0811   0.0607   1.0000
   7.500   1.0838   0.02049   0.01220  -0.0788   0.0459   1.0000
   7.750   1.0965   0.02139   0.01308  -0.0766   0.0353   1.0000
   8.000   1.1091   0.02231   0.01402  -0.0744   0.0266   1.0000
   8.250   1.1206   0.02333   0.01509  -0.0721   0.0203   1.0000
   8.500   1.1294   0.02459   0.01634  -0.0696   0.0152   1.0000
   8.750   1.1402   0.02573   0.01763  -0.0674   0.0126   1.0000
   9.000   1.1508   0.02693   0.01888  -0.0654   0.0102   1.0000
   9.250   1.1585   0.02841   0.02046  -0.0631   0.0083   1.0000
   9.500   1.1687   0.02972   0.02190  -0.0612   0.0074   1.0000
   9.750   1.1772   0.03124   0.02356  -0.0592   0.0068   1.0000
  10.000   1.1858   0.03282   0.02526  -0.0574   0.0063   1.0000
  10.250   1.1934   0.03455   0.02717  -0.0556   0.0058   1.0000
  10.500   1.1999   0.03649   0.02925  -0.0539   0.0056   1.0000
  10.750   1.2036   0.03895   0.03187  -0.0520   0.0052   1.0000
  11.000   1.2083   0.04158   0.03468  -0.0503   0.0051   1.0000
  11.250   1.2152   0.04388   0.03721  -0.0489   0.0050   1.0000
  11.500   1.2204   0.04647   0.04003  -0.0475   0.0049   1.0000
  11.750   1.2234   0.04931   0.04313  -0.0462   0.0048   1.0000
  12.000   1.2236   0.05247   0.04656  -0.0450   0.0047   1.0000
  12.250   1.2209   0.05598   0.05034  -0.0440   0.0047   1.0000
  12.500   1.2153   0.05982   0.05446  -0.0433   0.0046   1.0000
  12.750   1.2070   0.06404   0.05895  -0.0429   0.0046   1.0000
  13.000   1.1960   0.06872   0.06391  -0.0430   0.0046   1.0000
  13.250   1.1831   0.07381   0.06925  -0.0437   0.0046   1.0000
  13.500   1.1682   0.07945   0.07514  -0.0450   0.0046   1.0000
  13.750   1.1518   0.08566   0.08159  -0.0471   0.0046   1.0000
  14.000   1.1346   0.09246   0.08861  -0.0500   0.0046   1.0000
  14.250   1.1164   0.10002   0.09639  -0.0538   0.0046   1.0000
  14.500   1.0983   0.10826   0.10481  -0.0585   0.0047   1.0000
  14.750   1.0795   0.11758   0.11432  -0.0642   0.0047   1.0000
  15.000   1.0607   0.12795   0.12485  -0.0710   0.0048   1.0000
  15.250   1.0414   0.13972   0.13675  -0.0785   0.0048   1.0000
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