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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.65 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e472-il-1000000.txt
Download as CSV file: xf-e472-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -1.3187   0.07779   0.07431  -0.0272   1.0000   0.0251
 -18.000  -1.3880   0.06412   0.06037  -0.0347   1.0000   0.0238
 -17.750  -1.4428   0.05212   0.04811  -0.0418   1.0000   0.0233
 -17.500  -1.4760   0.04340   0.03916  -0.0476   1.0000   0.0232
 -17.250  -1.4968   0.03734   0.03294  -0.0513   1.0000   0.0237
 -17.000  -1.5085   0.03339   0.02887  -0.0527   1.0000   0.0244
 -16.750  -1.5145   0.03065   0.02603  -0.0526   1.0000   0.0252
 -16.500  -1.5160   0.02868   0.02396  -0.0516   1.0000   0.0262
 -16.250  -1.5173   0.02697   0.02217  -0.0499   1.0000   0.0273
 -16.000  -1.5189   0.02544   0.02059  -0.0475   1.0000   0.0287
 -15.750  -1.5157   0.02434   0.01942  -0.0450   1.0000   0.0300
 -15.500  -1.5088   0.02353   0.01853  -0.0425   1.0000   0.0312
 -15.250  -1.5073   0.02252   0.01749  -0.0391   1.0000   0.0331
 -15.000  -1.5031   0.02176   0.01670  -0.0356   1.0000   0.0348
 -14.750  -1.4955   0.02118   0.01606  -0.0325   1.0000   0.0363
 -14.500  -1.4858   0.02044   0.01529  -0.0298   1.0000   0.0383
 -14.250  -1.4740   0.01976   0.01460  -0.0274   1.0000   0.0405
 -14.000  -1.4589   0.01925   0.01404  -0.0254   1.0000   0.0422
 -13.750  -1.4446   0.01865   0.01340  -0.0232   1.0000   0.0444
 -13.500  -1.4296   0.01806   0.01280  -0.0212   1.0000   0.0468
 -13.250  -1.4121   0.01762   0.01232  -0.0195   1.0000   0.0488
 -13.000  -1.3952   0.01711   0.01179  -0.0176   1.0000   0.0514
 -12.750  -1.3779   0.01660   0.01128  -0.0159   1.0000   0.0541
 -12.500  -1.3587   0.01622   0.01086  -0.0143   1.0000   0.0563
 -12.250  -1.3394   0.01582   0.01042  -0.0128   1.0000   0.0584
 -12.000  -1.3209   0.01534   0.00995  -0.0111   1.0000   0.0615
 -11.750  -1.3008   0.01497   0.00956  -0.0097   1.0000   0.0639
 -11.500  -1.2794   0.01469   0.00923  -0.0084   1.0000   0.0656
 -11.250  -1.2599   0.01424   0.00878  -0.0068   1.0000   0.0688
 -11.000  -1.2393   0.01388   0.00843  -0.0054   1.0000   0.0717
 -10.750  -1.2176   0.01360   0.00812  -0.0041   1.0000   0.0742
 -10.500  -1.1957   0.01333   0.00782  -0.0028   1.0000   0.0761
 -10.250  -1.1750   0.01294   0.00744  -0.0014   1.0000   0.0797
 -10.000  -1.1531   0.01265   0.00715  -0.0002   1.0000   0.0828
  -9.750  -1.1302   0.01244   0.00691   0.0010   1.0000   0.0851
  -9.500  -1.1084   0.01213   0.00660   0.0023   1.0000   0.0888
  -9.250  -1.0861   0.01185   0.00634   0.0035   1.0000   0.0926
  -9.000  -1.0631   0.01164   0.00612   0.0046   1.0000   0.0954
  -8.750  -1.0395   0.01149   0.00593   0.0056   1.0000   0.0972
  -8.500  -1.0177   0.01115   0.00561   0.0070   1.0000   0.1014
  -8.250  -0.9948   0.01093   0.00541   0.0081   1.0000   0.1047
  -8.000  -0.9713   0.01076   0.00522   0.0092   1.0000   0.1074
  -7.750  -0.9473   0.01063   0.00506   0.0102   1.0000   0.1091
  -7.500  -0.9250   0.01034   0.00479   0.0115   1.0000   0.1135
  -7.250  -0.9017   0.01016   0.00463   0.0126   1.0000   0.1169
  -7.000  -0.8780   0.01001   0.00448   0.0137   1.0000   0.1199
  -6.750  -0.8540   0.00991   0.00434   0.0147   1.0000   0.1217
  -6.500  -0.8312   0.00969   0.00414   0.0159   1.0000   0.1258
  -6.250  -0.8078   0.00953   0.00402   0.0170   1.0000   0.1295
  -6.000  -0.7841   0.00942   0.00391   0.0181   1.0000   0.1325
  -5.750  -0.7573   0.00934   0.00382   0.0186   0.9997   0.1350
  -5.500  -0.7119   0.00917   0.00368   0.0150   0.9965   0.1401
  -5.250  -0.6649   0.00905   0.00360   0.0111   0.9935   0.1448
  -5.000  -0.6270   0.00892   0.00348   0.0093   0.9906   0.1482
  -4.750  -0.5907   0.00878   0.00335   0.0077   0.9875   0.1512
  -4.500  -0.5522   0.00858   0.00320   0.0057   0.9847   0.1564
  -4.250  -0.5123   0.00845   0.00310   0.0034   0.9825   0.1609
  -4.000  -0.4799   0.00830   0.00295   0.0028   0.9773   0.1637
  -3.750  -0.4433   0.00809   0.00277   0.0012   0.9714   0.1680
  -3.500  -0.4147   0.00789   0.00262   0.0014   0.9622   0.1727
  -3.250  -0.3854   0.00772   0.00247   0.0015   0.9479   0.1767
  -3.000  -0.3222   0.00748   0.00223  -0.0057   0.9243   0.1813
  -2.750  -0.2683   0.00749   0.00197  -0.0109   0.8236   0.1888
  -2.500  -0.2478   0.00773   0.00191  -0.0089   0.7347   0.1929
  -2.250  -0.2261   0.00796   0.00185  -0.0073   0.6549   0.1957
  -2.000  -0.2034   0.00809   0.00178  -0.0059   0.5830   0.2020
  -1.750  -0.1795   0.00824   0.00173  -0.0049   0.5176   0.2074
  -1.500  -0.1544   0.00838   0.00170  -0.0041   0.4651   0.2124
  -1.250  -0.1293   0.00843   0.00165  -0.0033   0.4205   0.2207
  -1.000  -0.1036   0.00853   0.00163  -0.0026   0.3817   0.2274
  -0.750  -0.0780   0.00857   0.00160  -0.0019   0.3473   0.2372
  -0.500  -0.0520   0.00862   0.00158  -0.0013   0.3186   0.2479
   0.000   0.0000   0.00866   0.00157   0.0000   0.2769   0.2768
   0.500   0.0520   0.00862   0.00158   0.0013   0.2478   0.3184
   0.750   0.0780   0.00857   0.00160   0.0019   0.2370   0.3474
   1.000   0.1036   0.00853   0.00163   0.0026   0.2275   0.3818
   1.250   0.1293   0.00843   0.00165   0.0033   0.2207   0.4207
   1.500   0.1544   0.00838   0.00170   0.0041   0.2125   0.4651
   1.750   0.1794   0.00824   0.00173   0.0049   0.2076   0.5182
   2.000   0.2033   0.00809   0.00178   0.0060   0.2020   0.5843
   2.250   0.2260   0.00796   0.00185   0.0073   0.1958   0.6556
   2.500   0.2478   0.00773   0.00191   0.0089   0.1929   0.7345
   2.750   0.2684   0.00749   0.00197   0.0109   0.1887   0.8234
   3.000   0.3233   0.00749   0.00223   0.0055   0.1811   0.9251
   3.250   0.3855   0.00772   0.00247  -0.0015   0.1767   0.9481
   3.500   0.4146   0.00789   0.00262  -0.0014   0.1728   0.9623
   3.750   0.4433   0.00809   0.00277  -0.0012   0.1681   0.9715
   4.000   0.4799   0.00830   0.00295  -0.0028   0.1637   0.9773
   4.250   0.5124   0.00845   0.00310  -0.0034   0.1609   0.9825
   4.500   0.5522   0.00858   0.00320  -0.0057   0.1564   0.9847
   4.750   0.5903   0.00878   0.00334  -0.0076   0.1514   0.9874
   5.000   0.6272   0.00893   0.00348  -0.0093   0.1482   0.9906
   5.250   0.6646   0.00905   0.00360  -0.0111   0.1449   0.9935
   5.500   0.7118   0.00917   0.00367  -0.0150   0.1401   0.9965
   5.750   0.7573   0.00934   0.00382  -0.0186   0.1350   0.9997
   6.000   0.7840   0.00942   0.00391  -0.0181   0.1326   1.0000
   6.250   0.8078   0.00953   0.00402  -0.0170   0.1295   1.0000
   6.500   0.8312   0.00969   0.00414  -0.0159   0.1258   1.0000
   6.750   0.8540   0.00990   0.00434  -0.0147   0.1217   1.0000
   7.000   0.8780   0.01001   0.00448  -0.0137   0.1199   1.0000
   7.250   0.9017   0.01016   0.00463  -0.0126   0.1170   1.0000
   7.500   0.9250   0.01034   0.00479  -0.0115   0.1135   1.0000
   7.750   0.9473   0.01063   0.00506  -0.0102   0.1091   1.0000
   8.000   0.9713   0.01076   0.00522  -0.0092   0.1075   1.0000
   8.250   0.9948   0.01093   0.00541  -0.0081   0.1047   1.0000
   8.500   1.0177   0.01115   0.00561  -0.0070   0.1014   1.0000
   8.750   1.0395   0.01149   0.00593  -0.0056   0.0972   1.0000
   9.000   1.0630   0.01165   0.00613  -0.0046   0.0955   1.0000
   9.250   1.0861   0.01185   0.00634  -0.0035   0.0926   1.0000
   9.500   1.1083   0.01213   0.00660  -0.0023   0.0886   1.0000
   9.750   1.1303   0.01243   0.00691  -0.0010   0.0851   1.0000
  10.000   1.1531   0.01265   0.00715   0.0002   0.0828   1.0000
  10.250   1.1750   0.01294   0.00743   0.0014   0.0797   1.0000
  10.500   1.1958   0.01332   0.00781   0.0028   0.0763   1.0000
  10.750   1.2177   0.01359   0.00812   0.0041   0.0742   1.0000
  11.000   1.2393   0.01388   0.00843   0.0054   0.0718   1.0000
  11.250   1.2599   0.01424   0.00878   0.0068   0.0689   1.0000
  11.500   1.2794   0.01469   0.00924   0.0084   0.0657   1.0000
  11.750   1.3008   0.01497   0.00956   0.0097   0.0639   1.0000
  12.000   1.3209   0.01533   0.00994   0.0111   0.0614   1.0000
  12.250   1.3395   0.01581   0.01041   0.0127   0.0584   1.0000
  12.500   1.3587   0.01622   0.01086   0.0143   0.0563   1.0000
  12.750   1.3780   0.01660   0.01128   0.0159   0.0541   1.0000
  13.000   1.3952   0.01711   0.01179   0.0176   0.0513   1.0000
  13.250   1.4121   0.01762   0.01232   0.0195   0.0488   1.0000
  13.500   1.4297   0.01806   0.01280   0.0212   0.0469   1.0000
  13.750   1.4447   0.01865   0.01340   0.0232   0.0444   1.0000
  14.000   1.4590   0.01925   0.01404   0.0254   0.0422   1.0000
  14.250   1.4740   0.01977   0.01460   0.0274   0.0403   1.0000
  14.500   1.4859   0.02044   0.01529   0.0298   0.0383   1.0000
  14.750   1.4957   0.02118   0.01607   0.0324   0.0363   1.0000
  15.000   1.5034   0.02176   0.01670   0.0356   0.0348   1.0000
  15.250   1.5080   0.02250   0.01748   0.0390   0.0332   1.0000
  15.500   1.5096   0.02351   0.01851   0.0423   0.0313   1.0000
  15.750   1.5162   0.02434   0.01942   0.0449   0.0301   1.0000
  16.000   1.5193   0.02545   0.02059   0.0474   0.0285   1.0000
  16.250   1.5183   0.02695   0.02215   0.0497   0.0272   1.0000
  16.500   1.5174   0.02862   0.02390   0.0514   0.0260   1.0000
  16.750   1.5158   0.03060   0.02597   0.0525   0.0252   1.0000
  17.000   1.5094   0.03338   0.02886   0.0525   0.0243   1.0000
  17.250   1.4976   0.03737   0.03297   0.0511   0.0237   1.0000
  17.500   1.4783   0.04323   0.03900   0.0476   0.0234   1.0000
  17.750   1.4441   0.05213   0.04811   0.0416   0.0232   1.0000
  18.000   1.3938   0.06347   0.05971   0.0348   0.0238   1.0000
  18.250   1.3211   0.07769   0.07420   0.0270   0.0248   1.0000
  18.500   1.2533   0.09116   0.08787   0.0196   0.0259   1.0000
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