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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 100,000
Max Cl/Cd: 33.6 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e472-il-100000-n5.txt
Download as CSV file: xf-e472-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 472 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -1.0040   0.06044   0.05406  -0.0384   1.0000   0.0942
 -13.000  -1.0640   0.05086   0.04414  -0.0436   1.0000   0.0945
 -12.750  -1.0947   0.04643   0.03941  -0.0427   1.0000   0.0956
 -12.500  -1.1191   0.04323   0.03586  -0.0395   1.0000   0.0971
 -12.250  -1.1068   0.04270   0.03544  -0.0377   1.0000   0.0989
 -12.000  -1.0984   0.04198   0.03472  -0.0355   1.0000   0.1010
 -11.750  -1.0941   0.04069   0.03331  -0.0333   1.0000   0.1032
 -11.500  -1.0927   0.03896   0.03133  -0.0308   1.0000   0.1059
 -11.250  -1.0934   0.03686   0.02883  -0.0281   1.0000   0.1088
 -11.000  -1.0780   0.03613   0.02813  -0.0265   1.0000   0.1111
 -10.750  -1.0621   0.03552   0.02751  -0.0249   1.0000   0.1136
 -10.500  -1.0489   0.03456   0.02642  -0.0231   1.0000   0.1165
 -10.250  -1.0381   0.03321   0.02480  -0.0210   1.0000   0.1199
 -10.000  -1.0247   0.03204   0.02341  -0.0192   1.0000   0.1230
  -9.750  -1.0057   0.03152   0.02292  -0.0178   1.0000   0.1256
  -9.500  -0.9881   0.03084   0.02217  -0.0163   1.0000   0.1286
  -9.250  -0.9719   0.02989   0.02102  -0.0146   1.0000   0.1323
  -9.000  -0.9560   0.02883   0.01968  -0.0128   1.0000   0.1361
  -8.750  -0.9356   0.02831   0.01921  -0.0116   1.0000   0.1388
  -8.500  -0.9159   0.02772   0.01858  -0.0102   1.0000   0.1420
  -8.250  -0.8969   0.02699   0.01769  -0.0087   1.0000   0.1459
  -8.000  -0.8782   0.02614   0.01658  -0.0072   1.0000   0.1501
  -7.750  -0.8569   0.02560   0.01611  -0.0060   1.0000   0.1530
  -7.500  -0.8360   0.02507   0.01554  -0.0047   1.0000   0.1565
  -7.250  -0.8153   0.02445   0.01480  -0.0034   1.0000   0.1607
  -7.000  -0.7946   0.02379   0.01393  -0.0021   1.0000   0.1650
  -6.750  -0.7728   0.02327   0.01348  -0.0009   1.0000   0.1683
  -6.500  -0.7510   0.02277   0.01296   0.0003   1.0000   0.1721
  -6.250  -0.7292   0.02224   0.01233   0.0015   1.0000   0.1766
  -6.000  -0.7073   0.02171   0.01168   0.0027   1.0000   0.1809
  -5.750  -0.6851   0.02124   0.01128   0.0039   1.0000   0.1847
  -5.500  -0.6628   0.02079   0.01081   0.0051   1.0000   0.1889
  -5.250  -0.6403   0.02035   0.01027   0.0062   1.0000   0.1938
  -5.000  -0.6179   0.01989   0.00981   0.0074   1.0000   0.1980
  -4.750  -0.5956   0.01949   0.00947   0.0085   1.0000   0.2025
  -4.500  -0.5730   0.01911   0.00906   0.0097   1.0000   0.2075
  -4.250  -0.5502   0.01874   0.00863   0.0108   1.0000   0.2125
  -4.000  -0.5280   0.01835   0.00835   0.0120   1.0000   0.2171
  -3.750  -0.5056   0.01803   0.00805   0.0132   1.0000   0.2228
  -3.500  -0.4829   0.01773   0.00772   0.0143   1.0000   0.2285
  -3.250  -0.4609   0.01738   0.00749   0.0155   1.0000   0.2336
  -3.000  -0.4388   0.01710   0.00725   0.0167   1.0000   0.2399
  -2.750  -0.4167   0.01684   0.00703   0.0179   1.0000   0.2465
  -2.500  -0.3952   0.01658   0.00688   0.0192   1.0000   0.2530
  -2.250  -0.3554   0.01635   0.00671   0.0168   0.9914   0.2624
  -2.000  -0.3103   0.01603   0.00653   0.0134   0.9739   0.2736
  -1.750  -0.2726   0.01566   0.00630   0.0116   0.9501   0.2852
  -1.500  -0.2350   0.01529   0.00605   0.0101   0.9210   0.2987
  -1.250  -0.1885   0.01491   0.00580   0.0069   0.8831   0.3163
  -1.000  -0.1276   0.01452   0.00549   0.0009   0.8158   0.3432
  -0.750  -0.0782   0.01436   0.00518  -0.0025   0.7158   0.3740
  -0.500  -0.0490   0.01442   0.00504  -0.0021   0.6266   0.4057
  -0.250  -0.0243   0.01448   0.00497  -0.0011   0.5531   0.4447
   0.000   0.0000   0.01450   0.00495   0.0000   0.4932   0.4933
   0.250   0.0243   0.01449   0.00497   0.0010   0.4446   0.5530
   0.500   0.0491   0.01441   0.00504   0.0021   0.4058   0.6268
   0.750   0.0782   0.01436   0.00518   0.0025   0.3738   0.7160
   1.000   0.1278   0.01452   0.00549  -0.0010   0.3432   0.8162
   1.250   0.1885   0.01491   0.00580  -0.0069   0.3163   0.8831
   1.500   0.2350   0.01529   0.00605  -0.0101   0.2987   0.9209
   1.750   0.2726   0.01566   0.00630  -0.0116   0.2853   0.9500
   2.000   0.3104   0.01603   0.00653  -0.0134   0.2736   0.9740
   2.250   0.3557   0.01635   0.00671  -0.0168   0.2624   0.9916
   2.500   0.3952   0.01658   0.00688  -0.0192   0.2530   1.0000
   2.750   0.4166   0.01684   0.00703  -0.0179   0.2464   1.0000
   3.000   0.4387   0.01710   0.00725  -0.0167   0.2398   1.0000
   3.250   0.4609   0.01737   0.00748  -0.0155   0.2335   1.0000
   3.500   0.4828   0.01772   0.00771  -0.0143   0.2286   1.0000
   3.750   0.5056   0.01803   0.00805  -0.0132   0.2228   1.0000
   4.000   0.5280   0.01835   0.00835  -0.0120   0.2171   1.0000
   4.250   0.5502   0.01873   0.00863  -0.0108   0.2125   1.0000
   4.500   0.5730   0.01911   0.00906  -0.0097   0.2075   1.0000
   4.750   0.5956   0.01949   0.00947  -0.0085   0.2025   1.0000
   5.000   0.6179   0.01989   0.00981  -0.0074   0.1980   1.0000
   5.250   0.6403   0.02035   0.01027  -0.0062   0.1938   1.0000
   5.500   0.6628   0.02079   0.01081  -0.0051   0.1889   1.0000
   5.750   0.6851   0.02124   0.01128  -0.0039   0.1847   1.0000
   6.000   0.7073   0.02171   0.01168  -0.0028   0.1810   1.0000
   6.250   0.7292   0.02225   0.01233  -0.0015   0.1766   1.0000
   6.500   0.7510   0.02277   0.01297  -0.0003   0.1721   1.0000
   6.750   0.7728   0.02327   0.01348   0.0009   0.1683   1.0000
   7.000   0.7947   0.02379   0.01393   0.0021   0.1650   1.0000
   7.250   0.8153   0.02445   0.01480   0.0034   0.1607   1.0000
   7.500   0.8360   0.02506   0.01554   0.0047   0.1565   1.0000
   7.750   0.8569   0.02560   0.01611   0.0060   0.1530   1.0000
   8.000   0.8783   0.02614   0.01658   0.0072   0.1501   1.0000
   8.250   0.8969   0.02699   0.01769   0.0087   0.1460   1.0000
   8.500   0.9159   0.02772   0.01858   0.0102   0.1420   1.0000
   8.750   0.9356   0.02831   0.01921   0.0116   0.1388   1.0000
   9.000   0.9560   0.02884   0.01968   0.0128   0.1361   1.0000
   9.250   0.9720   0.02990   0.02102   0.0146   0.1324   1.0000
   9.500   0.9881   0.03083   0.02216   0.0163   0.1286   1.0000
   9.750   1.0057   0.03153   0.02293   0.0178   0.1256   1.0000
  10.000   1.0248   0.03203   0.02339   0.0192   0.1230   1.0000
  10.250   1.0381   0.03322   0.02480   0.0210   0.1199   1.0000
  10.500   1.0490   0.03456   0.02642   0.0231   0.1165   1.0000
  10.750   1.0622   0.03552   0.02751   0.0249   0.1136   1.0000
  11.000   1.0782   0.03612   0.02812   0.0265   0.1111   1.0000
  11.250   1.0934   0.03687   0.02884   0.0281   0.1088   1.0000
  11.500   1.0929   0.03896   0.03133   0.0308   0.1059   1.0000
  11.750   1.0943   0.04069   0.03331   0.0333   0.1032   1.0000
  12.000   1.0987   0.04198   0.03472   0.0355   0.1010   1.0000
  12.250   1.1073   0.04269   0.03542   0.0376   0.0989   1.0000
  12.500   1.1190   0.04325   0.03589   0.0395   0.0970   1.0000
  12.750   1.0949   0.04644   0.03942   0.0427   0.0956   1.0000
  13.000   1.0648   0.05085   0.04413   0.0435   0.0945   1.0000
  13.250   1.0046   0.06045   0.05407   0.0383   0.0941   1.0000
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