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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 500,000
Max Cl/Cd: 109.23 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e431-il-500000-n5.txt
Download as CSV file: xf-e431-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 431 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0256   0.08862   0.08569  -0.1125   0.8527   0.0073
 -11.500  -0.1110   0.09579   0.09310  -0.1099   0.9199   0.0074
 -11.250  -0.0902   0.09127   0.08850  -0.1165   0.9082   0.0072
 -11.000  -0.0757   0.08648   0.08362  -0.1220   0.8927   0.0070
 -10.750  -0.0699   0.08183   0.07888  -0.1258   0.8751   0.0067
 -10.250  -0.1124   0.06423   0.06116  -0.1335   0.8442   0.0054
 -10.000  -0.1298   0.05636   0.05326  -0.1390   0.8319   0.0053
  -9.500  -0.1940   0.04146   0.03797  -0.1443   0.8092   0.0051
  -9.250  -0.2236   0.03716   0.03344  -0.1413   0.8002   0.0051
  -9.000  -0.2530   0.03281   0.02875  -0.1368   0.7917   0.0050
  -8.750  -0.2650   0.02894   0.02446  -0.1336   0.7857   0.0049
  -8.500  -0.2677   0.02544   0.02051  -0.1308   0.7802   0.0048
  -8.250  -0.2591   0.02307   0.01775  -0.1288   0.7753   0.0048
  -8.000  -0.2455   0.02114   0.01546  -0.1273   0.7710   0.0048
  -7.750  -0.2279   0.01966   0.01371  -0.1262   0.7669   0.0048
  -7.500  -0.2084   0.01839   0.01220  -0.1253   0.7628   0.0048
  -7.250  -0.1871   0.01742   0.01104  -0.1245   0.7591   0.0048
  -7.000  -0.1652   0.01651   0.00994  -0.1238   0.7556   0.0049
  -6.750  -0.1424   0.01578   0.00909  -0.1232   0.7521   0.0049
  -6.500  -0.1193   0.01510   0.00831  -0.1227   0.7483   0.0050
  -6.250  -0.0959   0.01447   0.00757  -0.1222   0.7449   0.0052
  -6.000  -0.0720   0.01396   0.00696  -0.1217   0.7416   0.0053
  -5.500  -0.0231   0.01302   0.00588  -0.1210   0.7352   0.0056
  -5.250   0.0018   0.01260   0.00542  -0.1208   0.7318   0.0060
  -5.000   0.0274   0.01227   0.00505  -0.1206   0.7285   0.0064
  -4.750   0.0533   0.01198   0.00469  -0.1204   0.7253   0.0071
  -4.250   0.1058   0.01144   0.00407  -0.1202   0.7193   0.0090
  -4.000   0.1323   0.01120   0.00380  -0.1202   0.7161   0.0111
  -3.750   0.1589   0.01097   0.00357  -0.1202   0.7127   0.0157
  -3.500   0.1853   0.01069   0.00337  -0.1202   0.7096   0.0317
  -3.250   0.2121   0.01044   0.00319  -0.1203   0.7067   0.0558
  -3.000   0.2388   0.01014   0.00304  -0.1205   0.7036   0.0936
  -2.750   0.2653   0.00977   0.00290  -0.1207   0.7001   0.1547
  -2.500   0.2919   0.00934   0.00275  -0.1210   0.6968   0.2445
  -2.250   0.3188   0.00885   0.00259  -0.1215   0.6936   0.3568
  -1.750   0.3730   0.00788   0.00254  -0.1222   0.6874   0.6526
  -1.500   0.4009   0.00790   0.00260  -0.1223   0.6838   0.6850
  -1.250   0.4289   0.00795   0.00262  -0.1223   0.6802   0.7024
  -1.000   0.4573   0.00802   0.00262  -0.1225   0.6769   0.7145
  -0.750   0.4854   0.00810   0.00267  -0.1226   0.6735   0.7279
  -0.500   0.5128   0.00820   0.00279  -0.1225   0.6697   0.7451
  -0.250   0.5395   0.00830   0.00291  -0.1221   0.6656   0.7563
   0.000   0.5679   0.00837   0.00291  -0.1224   0.6617   0.7620
   0.250   0.5957   0.00841   0.00291  -0.1225   0.6579   0.7640
   0.500   0.6234   0.00843   0.00293  -0.1226   0.6535   0.7659
   0.750   0.6510   0.00847   0.00295  -0.1227   0.6489   0.7680
   1.000   0.6786   0.00852   0.00296  -0.1228   0.6445   0.7700
   1.250   0.7063   0.00856   0.00299  -0.1229   0.6399   0.7721
   1.500   0.7338   0.00861   0.00302  -0.1230   0.6346   0.7744
   1.750   0.7612   0.00867   0.00304  -0.1231   0.6295   0.7767
   2.250   0.8153   0.00877   0.00313  -0.1232   0.6182   0.7803
   2.500   0.8416   0.00885   0.00318  -0.1230   0.6124   0.7820
   2.750   0.8682   0.00890   0.00327  -0.1230   0.6059   0.7839
   3.000   0.8940   0.00899   0.00333  -0.1227   0.5990   0.7861
   3.250   0.9202   0.00907   0.00342  -0.1226   0.5920   0.7884
   3.500   0.9457   0.00917   0.00350  -0.1223   0.5843   0.7907
   3.750   0.9714   0.00927   0.00360  -0.1221   0.5765   0.7929
   4.000   0.9963   0.00940   0.00370  -0.1218   0.5678   0.7950
   4.250   1.0208   0.00950   0.00382  -0.1213   0.5586   0.7968
   4.500   1.0440   0.00964   0.00396  -0.1206   0.5485   0.7988
   4.750   1.0667   0.00980   0.00411  -0.1198   0.5370   0.8011
   5.000   1.0890   0.00997   0.00427  -0.1189   0.5243   0.8037
   5.250   1.1105   0.01017   0.00445  -0.1179   0.5113   0.8064
   5.500   1.1309   0.01039   0.00464  -0.1167   0.4971   0.8090
   5.750   1.1497   0.01064   0.00486  -0.1152   0.4821   0.8115
   6.000   1.1654   0.01090   0.00509  -0.1130   0.4661   0.8138
   6.250   1.1802   0.01120   0.00537  -0.1108   0.4497   0.8165
   6.500   1.1944   0.01157   0.00569  -0.1084   0.4321   0.8195
   6.750   1.2074   0.01200   0.00607  -0.1060   0.4137   0.8229
   7.000   1.2197   0.01249   0.00649  -0.1034   0.3949   0.8265
   7.250   1.2320   0.01297   0.00694  -0.1009   0.3764   0.8296
   7.500   1.2429   0.01351   0.00744  -0.0983   0.3571   0.8331
   7.750   1.2532   0.01412   0.00800  -0.0957   0.3379   0.8368
   8.000   1.2634   0.01478   0.00860  -0.0931   0.3198   0.8408
   8.250   1.2732   0.01547   0.00926  -0.0906   0.3028   0.8445
   8.500   1.2824   0.01621   0.00996  -0.0881   0.2852   0.8487
   8.750   1.2910   0.01703   0.01074  -0.0856   0.2670   0.8537
   9.250   1.3083   0.01878   0.01245  -0.0810   0.2345   0.8641
   9.500   1.3166   0.01974   0.01339  -0.0788   0.2189   0.8701
   9.750   1.3251   0.02072   0.01436  -0.0767   0.2046   0.8763
  10.000   1.3317   0.02182   0.01543  -0.0744   0.1887   0.8839
  10.250   1.3392   0.02290   0.01651  -0.0723   0.1753   0.8927
  10.750   1.3515   0.02518   0.01882  -0.0680   0.1499   0.9251
  11.000   1.3586   0.02644   0.02008  -0.0664   0.1357   1.0000
  11.250   1.3666   0.02783   0.02144  -0.0651   0.1238   1.0000
  11.500   1.3743   0.02929   0.02287  -0.0637   0.1126   1.0000
  11.750   1.3826   0.03071   0.02429  -0.0625   0.1025   1.0000
  12.000   1.3908   0.03219   0.02576  -0.0614   0.0931   1.0000
  12.250   1.3980   0.03378   0.02734  -0.0602   0.0846   1.0000
  12.500   1.4044   0.03547   0.02902  -0.0591   0.0766   1.0000
  12.750   1.4120   0.03711   0.03067  -0.0581   0.0689   1.0000
  13.000   1.4188   0.03884   0.03242  -0.0572   0.0626   1.0000
  13.250   1.4243   0.04075   0.03432  -0.0563   0.0561   1.0000
  13.500   1.4305   0.04263   0.03623  -0.0554   0.0499   1.0000
  13.750   1.4361   0.04461   0.03823  -0.0547   0.0448   1.0000
  14.250   1.4463   0.04882   0.04250  -0.0534   0.0359   1.0000
  14.500   1.4504   0.05111   0.04482  -0.0529   0.0321   1.0000
  14.750   1.4557   0.05332   0.04708  -0.0524   0.0293   1.0000
  15.000   1.4592   0.05577   0.04957  -0.0521   0.0263   1.0000
  15.250   1.4629   0.05826   0.05212  -0.0518   0.0239   1.0000
  15.500   1.4664   0.06083   0.05476  -0.0516   0.0219   1.0000
  15.750   1.4695   0.06351   0.05750  -0.0516   0.0199   1.0000
  16.000   1.4712   0.06639   0.06045  -0.0516   0.0181   1.0000
  16.250   1.4731   0.06931   0.06344  -0.0517   0.0161   1.0000
  16.500   1.4741   0.07242   0.06662  -0.0519   0.0150   1.0000
  16.750   1.4755   0.07554   0.06982  -0.0523   0.0135   1.0000
  17.000   1.4753   0.07894   0.07330  -0.0527   0.0125   1.0000
  17.250   1.4754   0.08233   0.07677  -0.0533   0.0111   1.0000
  17.500   1.4747   0.08591   0.08045  -0.0540   0.0104   1.0000
  17.750   1.4726   0.08977   0.08439  -0.0549   0.0097   1.0000
  18.000   1.4717   0.09350   0.08823  -0.0558   0.0090   1.0000
  18.250   1.4697   0.09746   0.09230  -0.0570   0.0082   1.0000
  18.500   1.4660   0.10173   0.09665  -0.0583   0.0076   1.0000
  18.750   1.4634   0.10587   0.10091  -0.0597   0.0072   1.0000
  19.000   1.4601   0.11018   0.10532  -0.0612   0.0067   1.0000
  19.250   1.4561   0.11466   0.10991  -0.0629   0.0062   1.0000
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