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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 200,000
Max Cl/Cd: 41.37 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e472-il-200000.txt
Download as CSV file: xf-e472-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -1.0500   0.08283   0.07842  -0.0288   1.0000   0.0746
 -15.500  -1.1423   0.06419   0.05942  -0.0420   1.0000   0.0732
 -15.250  -1.1819   0.05556   0.05052  -0.0479   1.0000   0.0736
 -15.000  -1.2088   0.04979   0.04448  -0.0509   1.0000   0.0743
 -14.750  -1.2309   0.04554   0.03994  -0.0519   1.0000   0.0751
 -14.500  -1.2296   0.04345   0.03788  -0.0513   1.0000   0.0772
 -14.250  -1.2197   0.04265   0.03714  -0.0504   1.0000   0.0793
 -14.000  -1.2217   0.04101   0.03541  -0.0490   1.0000   0.0812
 -13.750  -1.2293   0.03923   0.03346  -0.0466   1.0000   0.0830
 -13.500  -1.2402   0.03757   0.03155  -0.0430   1.0000   0.0847
 -13.250  -1.2469   0.03602   0.02981  -0.0392   1.0000   0.0864
 -13.000  -1.2320   0.03537   0.02929  -0.0376   1.0000   0.0889
 -12.750  -1.2198   0.03497   0.02889  -0.0356   1.0000   0.0915
 -12.500  -1.2138   0.03406   0.02783  -0.0329   1.0000   0.0943
 -12.250  -1.2105   0.03303   0.02647  -0.0298   1.0000   0.0968
 -12.000  -1.1952   0.03197   0.02548  -0.0284   1.0000   0.0997
 -11.750  -1.1767   0.03179   0.02537  -0.0269   1.0000   0.1025
 -11.500  -1.1635   0.03115   0.02461  -0.0248   1.0000   0.1057
 -11.250  -1.1538   0.03024   0.02340  -0.0222   1.0000   0.1086
 -11.000  -1.1373   0.02912   0.02226  -0.0207   1.0000   0.1115
 -10.750  -1.1169   0.02886   0.02207  -0.0195   1.0000   0.1144
 -10.500  -1.0998   0.02830   0.02142  -0.0177   1.0000   0.1177
 -10.250  -1.0855   0.02755   0.02041  -0.0156   1.0000   0.1211
 -10.000  -1.0678   0.02649   0.01929  -0.0141   1.0000   0.1242
  -9.750  -1.0464   0.02612   0.01897  -0.0129   1.0000   0.1271
  -9.500  -1.0270   0.02565   0.01844  -0.0114   1.0000   0.1305
  -9.250  -1.0094   0.02503   0.01760  -0.0096   1.0000   0.1341
  -9.000  -0.9905   0.02409   0.01656  -0.0081   1.0000   0.1374
  -8.750  -0.9684   0.02367   0.01620  -0.0070   1.0000   0.1405
  -8.500  -0.9475   0.02325   0.01574  -0.0056   1.0000   0.1441
  -8.250  -0.9280   0.02277   0.01507  -0.0040   1.0000   0.1481
  -8.000  -0.9076   0.02194   0.01415  -0.0026   1.0000   0.1517
  -7.750  -0.8851   0.02148   0.01376  -0.0016   1.0000   0.1549
  -7.500  -0.8633   0.02112   0.01336  -0.0003   1.0000   0.1589
  -7.250  -0.8424   0.02071   0.01278   0.0012   1.0000   0.1630
  -7.000  -0.8208   0.01995   0.01196   0.0024   1.0000   0.1668
  -6.750  -0.7980   0.01952   0.01160   0.0035   1.0000   0.1704
  -6.500  -0.7757   0.01918   0.01122   0.0047   1.0000   0.1747
  -6.250  -0.7540   0.01884   0.01073   0.0061   1.0000   0.1790
  -6.000  -0.7313   0.01813   0.01003   0.0072   1.0000   0.1828
  -5.750  -0.7084   0.01775   0.00971   0.0083   1.0000   0.1869
  -5.500  -0.6858   0.01744   0.00936   0.0095   1.0000   0.1916
  -5.250  -0.6636   0.01720   0.00896   0.0109   1.0000   0.1958
  -5.000  -0.6403   0.01652   0.00840   0.0118   1.0000   0.2001
  -4.750  -0.6174   0.01622   0.00813   0.0130   1.0000   0.2047
  -4.500  -0.5948   0.01596   0.00781   0.0142   1.0000   0.2098
  -4.250  -0.5719   0.01551   0.00737   0.0153   1.0000   0.2144
  -4.000  -0.5491   0.01517   0.00710   0.0164   1.0000   0.2189
  -3.750  -0.5264   0.01493   0.00686   0.0176   1.0000   0.2243
  -3.500  -0.5039   0.01465   0.00655   0.0188   1.0000   0.2296
  -3.250  -0.4815   0.01432   0.00633   0.0200   1.0000   0.2350
  -3.000  -0.4591   0.01411   0.00615   0.0212   1.0000   0.2407
  -2.750  -0.4369   0.01387   0.00593   0.0224   1.0000   0.2466
  -2.500  -0.4153   0.01364   0.00581   0.0236   1.0000   0.2528
  -2.250  -0.3938   0.01352   0.00570   0.0249   1.0000   0.2599
  -2.000  -0.3462   0.01326   0.00561   0.0209   0.9925   0.2697
  -1.750  -0.2929   0.01296   0.00542   0.0159   0.9815   0.2824
  -1.500  -0.2458   0.01256   0.00515   0.0123   0.9655   0.2965
  -1.250  -0.2031   0.01210   0.00484   0.0098   0.9449   0.3122
  -1.000  -0.1619   0.01157   0.00451   0.0077   0.9175   0.3316
  -0.750  -0.0959   0.01094   0.00412   0.0005   0.8678   0.3679
  -0.500  -0.0349   0.01058   0.00373  -0.0054   0.7485   0.4236
  -0.250  -0.0151   0.01064   0.00361  -0.0031   0.6416   0.4799
   0.000   0.0000   0.01068   0.00358   0.0000   0.5521   0.5522
   0.250   0.0151   0.01064   0.00361   0.0031   0.4800   0.6416
   0.500   0.0349   0.01058   0.00373   0.0054   0.4236   0.7486
   0.750   0.0958   0.01095   0.00412  -0.0005   0.3677   0.8677
   1.000   0.1618   0.01157   0.00451  -0.0077   0.3318   0.9174
   1.250   0.2032   0.01210   0.00484  -0.0098   0.3122   0.9449
   1.500   0.2457   0.01256   0.00515  -0.0123   0.2965   0.9654
   1.750   0.2930   0.01296   0.00543  -0.0159   0.2825   0.9816
   2.000   0.3463   0.01326   0.00561  -0.0209   0.2697   0.9926
   2.250   0.3938   0.01353   0.00570  -0.0249   0.2599   1.0000
   2.500   0.4153   0.01364   0.00581  -0.0236   0.2529   1.0000
   2.750   0.4369   0.01388   0.00593  -0.0224   0.2466   1.0000
   3.000   0.4591   0.01411   0.00615  -0.0212   0.2407   1.0000
   3.250   0.4815   0.01431   0.00633  -0.0200   0.2350   1.0000
   3.500   0.5038   0.01464   0.00655  -0.0188   0.2296   1.0000
   3.750   0.5264   0.01492   0.00685  -0.0176   0.2243   1.0000
   4.000   0.5491   0.01517   0.00710  -0.0164   0.2190   1.0000
   4.250   0.5719   0.01551   0.00737  -0.0153   0.2144   1.0000
   4.500   0.5948   0.01596   0.00781  -0.0142   0.2099   1.0000
   4.750   0.6174   0.01622   0.00813  -0.0130   0.2047   1.0000
   5.000   0.6403   0.01652   0.00840  -0.0118   0.2001   1.0000
   5.250   0.6635   0.01719   0.00896  -0.0109   0.1958   1.0000
   5.500   0.6858   0.01744   0.00936  -0.0095   0.1916   1.0000
   5.750   0.7084   0.01775   0.00971  -0.0083   0.1869   1.0000
   6.000   0.7313   0.01813   0.01003  -0.0072   0.1828   1.0000
   6.250   0.7540   0.01883   0.01073  -0.0061   0.1790   1.0000
   6.500   0.7757   0.01917   0.01122  -0.0047   0.1747   1.0000
   6.750   0.7980   0.01953   0.01161  -0.0035   0.1704   1.0000
   7.000   0.8208   0.01995   0.01197  -0.0024   0.1668   1.0000
   7.250   0.8425   0.02071   0.01278  -0.0012   0.1631   1.0000
   7.500   0.8634   0.02112   0.01336   0.0003   0.1590   1.0000
   7.750   0.8851   0.02149   0.01376   0.0016   0.1550   1.0000
   8.000   0.9076   0.02194   0.01415   0.0026   0.1517   1.0000
   8.250   0.9280   0.02277   0.01507   0.0040   0.1481   1.0000
   8.500   0.9476   0.02325   0.01573   0.0056   0.1441   1.0000
   8.750   0.9685   0.02366   0.01620   0.0070   0.1405   1.0000
   9.000   0.9905   0.02410   0.01657   0.0081   0.1375   1.0000
   9.250   1.0095   0.02504   0.01760   0.0096   0.1341   1.0000
   9.500   1.0270   0.02566   0.01844   0.0114   0.1305   1.0000
   9.750   1.0464   0.02613   0.01899   0.0129   0.1271   1.0000
  10.000   1.0679   0.02647   0.01927   0.0141   0.1241   1.0000
  10.250   1.0855   0.02755   0.02041   0.0156   0.1210   1.0000
  10.500   1.0999   0.02830   0.02141   0.0177   0.1177   1.0000
  10.750   1.1170   0.02885   0.02206   0.0195   0.1144   1.0000
  11.000   1.1373   0.02912   0.02227   0.0207   0.1116   1.0000
  11.250   1.1538   0.03024   0.02339   0.0222   0.1086   1.0000
  11.500   1.1636   0.03113   0.02458   0.0248   0.1057   1.0000
  11.750   1.1769   0.03178   0.02535   0.0269   0.1025   1.0000
  12.000   1.1953   0.03197   0.02549   0.0283   0.0997   1.0000
  12.250   1.2107   0.03301   0.02645   0.0298   0.0968   1.0000
  12.500   1.2138   0.03408   0.02784   0.0329   0.0943   1.0000
  12.750   1.2202   0.03493   0.02885   0.0355   0.0915   1.0000
  13.000   1.2325   0.03533   0.02924   0.0376   0.0889   1.0000
  13.250   1.2474   0.03602   0.02981   0.0391   0.0864   1.0000
  13.500   1.2406   0.03757   0.03156   0.0429   0.0847   1.0000
  13.750   1.2297   0.03923   0.03346   0.0466   0.0830   1.0000
  14.000   1.2222   0.04100   0.03540   0.0489   0.0811   1.0000
  14.250   1.2215   0.04251   0.03699   0.0503   0.0792   1.0000
  14.500   1.2313   0.04336   0.03778   0.0512   0.0771   1.0000
  14.750   1.2315   0.04558   0.03998   0.0519   0.0751   1.0000
  15.000   1.2092   0.04981   0.04450   0.0508   0.0743   1.0000
  15.250   1.1826   0.05559   0.05055   0.0477   0.0736   1.0000
  15.500   1.1437   0.06413   0.05937   0.0419   0.0733   1.0000
  15.750   1.0004   0.09204   0.08774   0.0222   0.0755   1.0000
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