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EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 473 AIRFOIL (e473-il)
Reynolds number: 50,000
Max Cl/Cd: 21.38 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e473-il-50000-n5.txt
Download as CSV file: xf-e473-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 473 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6120   0.10851   0.09922  -0.0069   1.0000   0.1922
 -11.750  -0.6087   0.10539   0.09608  -0.0076   1.0000   0.1964
 -11.500  -0.6419   0.09720   0.08789  -0.0117   1.0000   0.2035
 -11.250  -0.6203   0.09682   0.08748  -0.0104   1.0000   0.2063
 -11.000  -0.6139   0.09429   0.08492  -0.0106   1.0000   0.2106
 -10.750  -0.6627   0.08412   0.07479  -0.0158   1.0000   0.2188
 -10.500  -0.6384   0.08425   0.07488  -0.0141   1.0000   0.2215
 -10.250  -0.7509   0.06587   0.05653  -0.0244   1.0000   0.2339
 -10.000  -0.7088   0.06808   0.05873  -0.0215   1.0000   0.2359
  -9.750  -0.6860   0.06820   0.05883  -0.0197   1.0000   0.2390
  -9.500  -0.8071   0.05505   0.04560  -0.0205   1.0000   0.2473
  -9.250  -0.8351   0.05103   0.04143  -0.0176   1.0000   0.2518
  -9.000  -0.8145   0.05051   0.04093  -0.0164   1.0000   0.2555
  -8.750  -0.8162   0.04840   0.03871  -0.0142   1.0000   0.2602
  -8.500  -0.8464   0.04426   0.03416  -0.0102   1.0000   0.2664
  -8.250  -0.8206   0.04398   0.03398  -0.0093   1.0000   0.2698
  -8.000  -0.8054   0.04300   0.03295  -0.0077   1.0000   0.2740
  -7.750  -0.8014   0.04122   0.03099  -0.0054   1.0000   0.2793
  -7.500  -0.7983   0.03932   0.02886  -0.0029   1.0000   0.2845
  -7.250  -0.7768   0.03877   0.02836  -0.0017   1.0000   0.2884
  -7.000  -0.7621   0.03773   0.02724   0.0000   1.0000   0.2930
  -6.750  -0.7545   0.03615   0.02542   0.0022   1.0000   0.2986
  -6.500  -0.7378   0.03521   0.02443   0.0037   1.0000   0.3029
  -6.250  -0.7182   0.03455   0.02380   0.0051   1.0000   0.3071
  -6.000  -0.7029   0.03358   0.02271   0.0067   1.0000   0.3123
  -5.750  -0.6913   0.03233   0.02123   0.0087   1.0000   0.3179
  -5.500  -0.6698   0.03179   0.02079   0.0099   1.0000   0.3217
  -5.250  -0.6511   0.03113   0.02014   0.0113   1.0000   0.3264
  -5.000  -0.6353   0.03028   0.01915   0.0129   1.0000   0.3320
  -4.750  -0.6181   0.02952   0.01833   0.0144   1.0000   0.3367
  -4.500  -0.5984   0.02901   0.01791   0.0158   1.0000   0.3411
  -4.250  -0.5807   0.02842   0.01730   0.0172   1.0000   0.3463
  -4.000  -0.5653   0.02775   0.01647   0.0189   1.0000   0.3523
  -3.750  -0.5466   0.02734   0.01620   0.0202   1.0000   0.3564
  -3.500  -0.5089   0.02690   0.01579   0.0178   0.9876   0.3629
  -3.250  -0.4611   0.02629   0.01510   0.0135   0.9596   0.3711
  -3.000  -0.4157   0.02578   0.01470   0.0103   0.9268   0.3780
  -2.750  -0.3695   0.02517   0.01399   0.0070   0.8915   0.3868
  -2.500  -0.3185   0.02465   0.01355   0.0031   0.8500   0.3946
  -2.250  -0.2676   0.02415   0.01287  -0.0006   0.7999   0.4048
  -2.000  -0.2229   0.02382   0.01244  -0.0029   0.7440   0.4129
  -1.500  -0.1600   0.02355   0.01171  -0.0030   0.6485   0.4303
  -1.250  -0.1335   0.02351   0.01141  -0.0024   0.6121   0.4405
  -1.000  -0.1064   0.02347   0.01127  -0.0019   0.5822   0.4494
  -0.750  -0.0799   0.02345   0.01110  -0.0014   0.5562   0.4604
  -0.500  -0.0531   0.02343   0.01101  -0.0009   0.5346   0.4720
  -0.250  -0.0263   0.02342   0.01096  -0.0005   0.5158   0.4849
   0.000   0.0000   0.02342   0.01094   0.0000   0.4995   0.4995
   0.250   0.0263   0.02342   0.01096   0.0005   0.4849   0.5158
   0.500   0.0531   0.02343   0.01101   0.0009   0.4720   0.5346
   0.750   0.0799   0.02345   0.01110   0.0014   0.4605   0.5563
   1.000   0.1064   0.02347   0.01127   0.0019   0.4494   0.5822
   1.250   0.1334   0.02350   0.01141   0.0024   0.4404   0.6120
   1.500   0.1600   0.02355   0.01171   0.0030   0.4302   0.6484
   2.000   0.2229   0.02382   0.01244   0.0029   0.4129   0.7440
   2.250   0.2676   0.02415   0.01287   0.0006   0.4048   0.8000
   2.500   0.3185   0.02464   0.01355  -0.0031   0.3946   0.8500
   2.750   0.3694   0.02516   0.01399  -0.0070   0.3868   0.8914
   3.000   0.4158   0.02578   0.01470  -0.0103   0.3780   0.9269
   3.250   0.4610   0.02629   0.01510  -0.0135   0.3712   0.9596
   3.500   0.5089   0.02689   0.01579  -0.0178   0.3629   0.9876
   3.750   0.5466   0.02733   0.01619  -0.0202   0.3564   1.0000
   4.000   0.5653   0.02775   0.01647  -0.0189   0.3523   1.0000
   4.250   0.5807   0.02843   0.01730  -0.0172   0.3463   1.0000
   4.500   0.5983   0.02901   0.01790  -0.0158   0.3411   1.0000
   4.750   0.6181   0.02952   0.01833  -0.0144   0.3367   1.0000
   5.000   0.6353   0.03028   0.01915  -0.0129   0.3320   1.0000
   5.250   0.6511   0.03113   0.02014  -0.0113   0.3264   1.0000
   5.500   0.6698   0.03178   0.02078  -0.0099   0.3217   1.0000
   5.750   0.6913   0.03233   0.02123  -0.0087   0.3179   1.0000
   6.000   0.7029   0.03357   0.02271  -0.0067   0.3123   1.0000
   6.250   0.7182   0.03454   0.02379  -0.0051   0.3071   1.0000
   6.500   0.7378   0.03521   0.02443  -0.0037   0.3029   1.0000
   6.750   0.7544   0.03615   0.02542  -0.0022   0.2986   1.0000
   7.000   0.7621   0.03772   0.02723   0.0000   0.2930   1.0000
   7.250   0.7769   0.03875   0.02834   0.0017   0.2883   1.0000
   7.500   0.7983   0.03932   0.02886   0.0029   0.2845   1.0000
   7.750   0.8014   0.04121   0.03098   0.0054   0.2793   1.0000
   8.000   0.8054   0.04301   0.03296   0.0077   0.2740   1.0000
   8.250   0.8208   0.04397   0.03396   0.0092   0.2698   1.0000
   8.500   0.8469   0.04423   0.03413   0.0101   0.2665   1.0000
   8.750   0.8164   0.04840   0.03870   0.0141   0.2602   1.0000
   9.000   0.8149   0.05049   0.04091   0.0163   0.2554   1.0000
   9.250   0.8353   0.05103   0.04144   0.0176   0.2518   1.0000
   9.500   0.8068   0.05509   0.04564   0.0205   0.2473   1.0000
   9.750   0.6866   0.06819   0.05882   0.0197   0.2390   1.0000
  10.000   0.7091   0.06811   0.05876   0.0214   0.2359   1.0000
  10.250   0.7518   0.06583   0.05649   0.0244   0.2339   1.0000
  10.500   0.6391   0.08426   0.07489   0.0140   0.2215   1.0000
  10.750   0.6642   0.08399   0.07466   0.0158   0.2187   1.0000
  11.250   0.6214   0.09678   0.08744   0.0103   0.2063   1.0000
  11.500   0.6439   0.09701   0.08771   0.0117   0.2034   1.0000
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