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EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 472 AIRFOIL (e472-il)
Reynolds number: 50,000
Max Cl/Cd: 21.87 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e472-il-50000-n5.txt
Download as CSV file: xf-e472-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6555   0.10121   0.09234  -0.0046   1.0000   0.1432
 -10.750  -0.6741   0.09436   0.08551  -0.0083   1.0000   0.1465
 -10.500  -0.7699   0.07428   0.06551  -0.0231   1.0000   0.1502
 -10.250  -0.7221   0.07864   0.06986  -0.0173   1.0000   0.1525
 -10.000  -0.7516   0.07083   0.06204  -0.0217   1.0000   0.1551
  -9.750  -0.8036   0.06313   0.05428  -0.0228   1.0000   0.1569
  -9.500  -0.8373   0.05742   0.04835  -0.0218   1.0000   0.1596
  -9.250  -0.8674   0.05188   0.04238  -0.0199   1.0000   0.1631
  -9.000  -0.8641   0.04940   0.03974  -0.0182   1.0000   0.1664
  -8.750  -0.8475   0.04828   0.03859  -0.0169   1.0000   0.1697
  -8.500  -0.8395   0.04619   0.03631  -0.0152   1.0000   0.1734
  -8.250  -0.8384   0.04333   0.03305  -0.0132   1.0000   0.1780
  -8.000  -0.8261   0.04159   0.03114  -0.0116   1.0000   0.1820
  -7.750  -0.8077   0.04055   0.03007  -0.0103   1.0000   0.1859
  -7.500  -0.7937   0.03894   0.02826  -0.0087   1.0000   0.1903
  -7.250  -0.7841   0.03685   0.02569  -0.0068   1.0000   0.1957
  -7.000  -0.7625   0.03602   0.02497  -0.0057   1.0000   0.1996
  -6.750  -0.7437   0.03498   0.02385  -0.0043   1.0000   0.2043
  -6.500  -0.7272   0.03355   0.02212  -0.0028   1.0000   0.2097
  -6.250  -0.7079   0.03242   0.02089  -0.0015   1.0000   0.2143
  -6.000  -0.6868   0.03160   0.02009  -0.0003   1.0000   0.2192
  -5.750  -0.6675   0.03056   0.01885   0.0010   1.0000   0.2253
  -5.500  -0.6468   0.02957   0.01774   0.0022   1.0000   0.2304
  -5.250  -0.6249   0.02882   0.01702   0.0033   1.0000   0.2356
  -5.000  -0.6039   0.02798   0.01603   0.0045   1.0000   0.2423
  -4.750  -0.5819   0.02721   0.01523   0.0056   1.0000   0.2480
  -4.500  -0.5595   0.02652   0.01456   0.0067   1.0000   0.2539
  -4.250  -0.5375   0.02579   0.01365   0.0078   1.0000   0.2612
  -4.000  -0.5146   0.02519   0.01318   0.0088   1.0000   0.2674
  -3.750  -0.4919   0.02459   0.01253   0.0098   1.0000   0.2752
  -3.500  -0.4687   0.02400   0.01199   0.0108   1.0000   0.2821
  -3.250  -0.4455   0.02347   0.01149   0.0117   1.0000   0.2903
  -3.000  -0.4221   0.02297   0.01104   0.0127   1.0000   0.2991
  -2.750  -0.3985   0.02251   0.01062   0.0135   1.0000   0.3089
  -2.500  -0.3746   0.02206   0.01027   0.0143   1.0000   0.3184
  -2.250  -0.3504   0.02166   0.00992   0.0151   1.0000   0.3301
  -2.000  -0.3264   0.02127   0.00966   0.0158   1.0000   0.3430
  -1.750  -0.3032   0.02090   0.00944   0.0166   1.0000   0.3570
  -1.500  -0.2812   0.02056   0.00927   0.0177   1.0000   0.3727
  -1.250  -0.2599   0.02024   0.00915   0.0188   1.0000   0.3917
  -1.000  -0.2339   0.01994   0.00909   0.0189   0.9964   0.4163
  -0.750  -0.1790   0.01941   0.00899   0.0136   0.9607   0.4605
  -0.500  -0.1349   0.01876   0.00881   0.0110   0.9153   0.5185
  -0.250  -0.0824   0.01803   0.00867   0.0075   0.8585   0.6079
   0.000   0.0000   0.01750   0.00863   0.0000   0.7527   0.7528
   0.250   0.0824   0.01803   0.00867  -0.0075   0.6079   0.8584
   0.500   0.1349   0.01877   0.00881  -0.0109   0.5183   0.9153
   0.750   0.1790   0.01941   0.00899  -0.0135   0.4602   0.9607
   1.000   0.2341   0.01994   0.00909  -0.0189   0.4162   0.9965
   1.250   0.2599   0.02024   0.00915  -0.0188   0.3918   1.0000
   1.500   0.2811   0.02056   0.00927  -0.0177   0.3727   1.0000
   1.750   0.3032   0.02090   0.00944  -0.0166   0.3571   1.0000
   2.000   0.3264   0.02127   0.00966  -0.0158   0.3431   1.0000
   2.250   0.3503   0.02166   0.00992  -0.0151   0.3302   1.0000
   2.500   0.3746   0.02206   0.01028  -0.0143   0.3184   1.0000
   2.750   0.3986   0.02251   0.01062  -0.0135   0.3089   1.0000
   3.000   0.4221   0.02297   0.01104  -0.0127   0.2990   1.0000
   3.250   0.4455   0.02347   0.01149  -0.0117   0.2904   1.0000
   3.500   0.4687   0.02400   0.01199  -0.0108   0.2822   1.0000
   3.750   0.4919   0.02459   0.01253  -0.0098   0.2752   1.0000
   4.000   0.5146   0.02518   0.01317  -0.0088   0.2674   1.0000
   4.250   0.5375   0.02579   0.01365  -0.0078   0.2612   1.0000
   4.500   0.5595   0.02652   0.01456  -0.0067   0.2539   1.0000
   4.750   0.5819   0.02721   0.01523  -0.0056   0.2480   1.0000
   5.000   0.6039   0.02798   0.01602  -0.0045   0.2423   1.0000
   5.250   0.6249   0.02882   0.01702  -0.0033   0.2356   1.0000
   5.500   0.6468   0.02957   0.01774  -0.0022   0.2304   1.0000
   6.000   0.6868   0.03161   0.02009   0.0003   0.2193   1.0000
   6.250   0.7079   0.03242   0.02089   0.0015   0.2143   1.0000
   6.500   0.7272   0.03355   0.02213   0.0028   0.2096   1.0000
   6.750   0.7437   0.03497   0.02385   0.0043   0.2043   1.0000
   7.000   0.7625   0.03602   0.02497   0.0057   0.1996   1.0000
   7.250   0.7842   0.03684   0.02569   0.0068   0.1957   1.0000
   7.500   0.7937   0.03894   0.02826   0.0087   0.1904   1.0000
   7.750   0.8077   0.04055   0.03008   0.0103   0.1859   1.0000
   8.000   0.8262   0.04158   0.03113   0.0116   0.1820   1.0000
   8.250   0.8386   0.04332   0.03303   0.0132   0.1781   1.0000
   8.500   0.8395   0.04619   0.03631   0.0152   0.1734   1.0000
   8.750   0.8475   0.04830   0.03861   0.0169   0.1697   1.0000
   9.000   0.8637   0.04947   0.03981   0.0182   0.1664   1.0000
   9.250   0.8678   0.05185   0.04235   0.0198   0.1632   1.0000
   9.500   0.8375   0.05740   0.04834   0.0218   0.1596   1.0000
   9.750   0.8037   0.06316   0.05431   0.0227   0.1570   1.0000
  10.000   0.7527   0.07074   0.06195   0.0217   0.1550   1.0000
  10.250   0.7240   0.07840   0.06961   0.0174   0.1525   1.0000
  10.500   0.7682   0.07459   0.06583   0.0228   0.1502   1.0000
  10.750   0.6749   0.09435   0.08550   0.0082   0.1466   1.0000
  11.000   0.6563   0.10120   0.09233   0.0045   0.1432   1.0000
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