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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 200,000
Max Cl/Cd: 49.29 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e472-il-200000-n5.txt
Download as CSV file: xf-e472-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9728   0.11222   0.10772  -0.0069   1.0000   0.0540
 -16.500  -1.0422   0.09579   0.09108  -0.0164   1.0000   0.0548
 -16.250  -1.0874   0.08473   0.07987  -0.0227   1.0000   0.0553
 -16.000  -1.1263   0.07501   0.06998  -0.0283   1.0000   0.0558
 -15.750  -1.1583   0.06652   0.06131  -0.0333   1.0000   0.0563
 -15.500  -1.1843   0.05902   0.05363  -0.0379   1.0000   0.0568
 -15.250  -1.2053   0.05245   0.04690  -0.0420   1.0000   0.0576
 -15.000  -1.2212   0.04702   0.04136  -0.0453   1.0000   0.0584
 -14.750  -1.2330   0.04271   0.03691  -0.0475   1.0000   0.0593
 -14.500  -1.2409   0.03943   0.03351  -0.0483   1.0000   0.0607
 -14.250  -1.2453   0.03693   0.03087  -0.0481   1.0000   0.0623
 -14.000  -1.2471   0.03496   0.02874  -0.0470   1.0000   0.0640
 -13.750  -1.2459   0.03336   0.02694  -0.0453   1.0000   0.0658
 -13.500  -1.2464   0.03196   0.02552  -0.0430   1.0000   0.0674
 -13.250  -1.2437   0.03085   0.02435  -0.0404   1.0000   0.0693
 -13.000  -1.2393   0.02990   0.02330  -0.0377   1.0000   0.0714
 -12.750  -1.2331   0.02902   0.02228  -0.0349   1.0000   0.0738
 -12.500  -1.2243   0.02814   0.02129  -0.0324   1.0000   0.0762
 -12.250  -1.2140   0.02738   0.02052  -0.0301   1.0000   0.0786
 -12.000  -1.2010   0.02669   0.01974  -0.0281   1.0000   0.0814
 -11.750  -1.1865   0.02600   0.01890  -0.0262   1.0000   0.0843
 -11.500  -1.1719   0.02528   0.01809  -0.0243   1.0000   0.0868
 -11.250  -1.1569   0.02466   0.01747  -0.0224   1.0000   0.0894
 -11.000  -1.1401   0.02410   0.01683  -0.0207   1.0000   0.0921
 -10.750  -1.1223   0.02352   0.01611  -0.0191   1.0000   0.0952
 -10.500  -1.1044   0.02292   0.01541  -0.0175   1.0000   0.0978
 -10.250  -1.0867   0.02239   0.01488  -0.0158   1.0000   0.1005
 -10.000  -1.0676   0.02191   0.01435  -0.0143   1.0000   0.1034
  -9.750  -1.0479   0.02143   0.01375  -0.0129   1.0000   0.1065
  -9.500  -1.0277   0.02095   0.01314  -0.0115   1.0000   0.1094
  -9.250  -1.0084   0.02046   0.01267  -0.0100   1.0000   0.1122
  -9.000  -0.9880   0.02006   0.01224  -0.0086   1.0000   0.1152
  -8.750  -0.9669   0.01966   0.01176  -0.0073   1.0000   0.1186
  -8.500  -0.9454   0.01927   0.01123  -0.0060   1.0000   0.1217
  -8.250  -0.9248   0.01882   0.01081  -0.0046   1.0000   0.1246
  -8.000  -0.9035   0.01847   0.01045  -0.0033   1.0000   0.1278
  -7.750  -0.8816   0.01814   0.01005  -0.0020   1.0000   0.1313
  -7.500  -0.8593   0.01780   0.00961  -0.0008   1.0000   0.1347
  -7.250  -0.8377   0.01741   0.00923   0.0005   1.0000   0.1377
  -7.000  -0.8158   0.01710   0.00892   0.0017   1.0000   0.1410
  -6.750  -0.7934   0.01681   0.00859   0.0029   1.0000   0.1446
  -6.500  -0.7707   0.01652   0.00823   0.0041   1.0000   0.1482
  -6.250  -0.7484   0.01619   0.00788   0.0053   1.0000   0.1513
  -6.000  -0.7262   0.01589   0.00761   0.0066   1.0000   0.1548
  -5.750  -0.7035   0.01564   0.00735   0.0078   1.0000   0.1585
  -5.500  -0.6807   0.01539   0.00705   0.0089   1.0000   0.1622
  -5.250  -0.6579   0.01512   0.00676   0.0101   1.0000   0.1656
  -5.000  -0.6357   0.01484   0.00653   0.0113   1.0000   0.1692
  -4.750  -0.6130   0.01462   0.00632   0.0125   1.0000   0.1732
  -4.500  -0.5902   0.01441   0.00608   0.0137   1.0000   0.1771
  -4.250  -0.5674   0.01420   0.00586   0.0149   1.0000   0.1806
  -4.000  -0.5453   0.01395   0.00568   0.0162   1.0000   0.1846
  -3.750  -0.5177   0.01376   0.00552   0.0163   0.9985   0.1894
  -3.500  -0.4704   0.01360   0.00534   0.0124   0.9897   0.1952
  -3.250  -0.4286   0.01331   0.00515   0.0096   0.9801   0.2007
  -3.000  -0.3930   0.01306   0.00494   0.0083   0.9669   0.2070
  -2.750  -0.3626   0.01281   0.00471   0.0081   0.9488   0.2126
  -2.500  -0.3274   0.01250   0.00448   0.0069   0.9279   0.2186
  -2.250  -0.2804   0.01225   0.00425   0.0034   0.8989   0.2272
  -2.000  -0.2041   0.01190   0.00388  -0.0062   0.8270   0.2395
  -1.750  -0.1615   0.01194   0.00361  -0.0086   0.7245   0.2488
  -1.500  -0.1378   0.01210   0.00349  -0.0073   0.6430   0.2582
  -1.250  -0.1160   0.01226   0.00340  -0.0057   0.5717   0.2683
  -1.000  -0.0937   0.01240   0.00333  -0.0043   0.5102   0.2800
  -0.750  -0.0709   0.01250   0.00327  -0.0031   0.4584   0.2936
  -0.500  -0.0475   0.01256   0.00324  -0.0020   0.4171   0.3092
  -0.250  -0.0237   0.01260   0.00322  -0.0010   0.3826   0.3289
   0.000   0.0000   0.01260   0.00321   0.0000   0.3533   0.3533
   0.250   0.0237   0.01260   0.00322   0.0010   0.3290   0.3826
   0.500   0.0475   0.01256   0.00324   0.0020   0.3092   0.4171
   0.750   0.0709   0.01250   0.00327   0.0031   0.2935   0.4583
   1.000   0.0937   0.01240   0.00333   0.0043   0.2801   0.5098
   1.250   0.1160   0.01226   0.00340   0.0057   0.2683   0.5720
   1.500   0.1378   0.01210   0.00349   0.0073   0.2582   0.6429
   1.750   0.1615   0.01194   0.00361   0.0086   0.2489   0.7247
   2.000   0.2046   0.01190   0.00388   0.0061   0.2394   0.8280
   2.250   0.2805   0.01225   0.00425  -0.0034   0.2271   0.8990
   2.500   0.3273   0.01250   0.00448  -0.0069   0.2187   0.9279
   2.750   0.3626   0.01281   0.00471  -0.0081   0.2126   0.9486
   3.000   0.3930   0.01306   0.00494  -0.0083   0.2070   0.9672
   3.250   0.4287   0.01331   0.00515  -0.0097   0.2008   0.9803
   3.500   0.4701   0.01359   0.00534  -0.0124   0.1953   0.9896
   3.750   0.5179   0.01376   0.00552  -0.0163   0.1893   0.9986
   4.000   0.5453   0.01395   0.00568  -0.0162   0.1847   1.0000
   4.250   0.5674   0.01420   0.00586  -0.0149   0.1807   1.0000
   4.500   0.5902   0.01441   0.00608  -0.0137   0.1771   1.0000
   4.750   0.6130   0.01461   0.00632  -0.0125   0.1732   1.0000
   5.000   0.6357   0.01484   0.00653  -0.0113   0.1693   1.0000
   5.250   0.6579   0.01512   0.00676  -0.0101   0.1656   1.0000
   5.500   0.6807   0.01539   0.00705  -0.0089   0.1622   1.0000
   5.750   0.7035   0.01563   0.00734  -0.0078   0.1585   1.0000
   6.000   0.7262   0.01589   0.00761  -0.0066   0.1548   1.0000
   6.250   0.7484   0.01618   0.00788  -0.0053   0.1513   1.0000
   6.500   0.7707   0.01652   0.00823  -0.0041   0.1481   1.0000
   6.750   0.7934   0.01681   0.00859  -0.0029   0.1447   1.0000
   7.000   0.8158   0.01710   0.00892  -0.0017   0.1411   1.0000
   7.250   0.8377   0.01741   0.00923  -0.0005   0.1377   1.0000
   7.500   0.8593   0.01780   0.00961   0.0008   0.1347   1.0000
   7.750   0.8816   0.01814   0.01005   0.0020   0.1314   1.0000
   8.000   0.9035   0.01847   0.01045   0.0033   0.1278   1.0000
   8.250   0.9248   0.01882   0.01081   0.0046   0.1246   1.0000
   8.500   0.9454   0.01926   0.01123   0.0060   0.1217   1.0000
   8.750   0.9670   0.01966   0.01175   0.0073   0.1185   1.0000
   9.000   0.9880   0.02005   0.01224   0.0086   0.1152   1.0000
   9.250   1.0084   0.02046   0.01268   0.0100   0.1122   1.0000
   9.500   1.0277   0.02095   0.01314   0.0115   0.1095   1.0000
   9.750   1.0479   0.02143   0.01375   0.0129   0.1065   1.0000
  10.000   1.0677   0.02191   0.01435   0.0143   0.1034   1.0000
  10.250   1.0867   0.02238   0.01488   0.0158   0.1005   1.0000
  10.500   1.1044   0.02292   0.01541   0.0175   0.0979   1.0000
  10.750   1.1224   0.02352   0.01611   0.0191   0.0951   1.0000
  11.000   1.1401   0.02410   0.01683   0.0207   0.0921   1.0000
  11.250   1.1569   0.02466   0.01747   0.0224   0.0894   1.0000
  11.500   1.1720   0.02528   0.01809   0.0243   0.0868   1.0000
  11.750   1.1866   0.02600   0.01890   0.0262   0.0843   1.0000
  12.000   1.2012   0.02669   0.01974   0.0281   0.0814   1.0000
  12.250   1.2142   0.02737   0.02051   0.0301   0.0786   1.0000
  12.500   1.2245   0.02814   0.02129   0.0324   0.0762   1.0000
  12.750   1.2334   0.02901   0.02228   0.0348   0.0738   1.0000
  13.000   1.2398   0.02989   0.02329   0.0376   0.0714   1.0000
  13.250   1.2441   0.03084   0.02434   0.0404   0.0692   1.0000
  13.500   1.2468   0.03195   0.02551   0.0429   0.0674   1.0000
  13.750   1.2465   0.03334   0.02693   0.0452   0.0658   1.0000
  14.000   1.2478   0.03494   0.02872   0.0469   0.0639   1.0000
  14.250   1.2461   0.03692   0.03086   0.0480   0.0622   1.0000
  14.500   1.2418   0.03940   0.03348   0.0483   0.0607   1.0000
  14.750   1.2340   0.04267   0.03687   0.0474   0.0594   1.0000
  15.000   1.2223   0.04698   0.04131   0.0452   0.0583   1.0000
  15.250   1.2066   0.05239   0.04684   0.0419   0.0575   1.0000
  15.500   1.1862   0.05888   0.05348   0.0378   0.0568   1.0000
  15.750   1.1592   0.06659   0.06138   0.0331   0.0561   1.0000
  16.000   1.1269   0.07514   0.07011   0.0280   0.0557   1.0000
  16.250   1.0885   0.08479   0.07993   0.0225   0.0552   1.0000
  16.500   1.0444   0.09565   0.09094   0.0163   0.0547   1.0000
  16.750   0.9752   0.11206   0.10756   0.0068   0.0539   1.0000
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