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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 1,000,000
Max Cl/Cd: 144.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e431-il-1000000.txt
Download as CSV file: xf-e431-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1189   0.09331   0.09149  -0.1074   0.9410   0.0099
 -11.000  -0.1007   0.08621   0.08434  -0.1166   0.9337   0.0101
  -7.000  -0.1515   0.01761   0.01236  -0.1277   0.7626   0.0077
  -6.750  -0.1290   0.01639   0.01106  -0.1271   0.7589   0.0072
  -6.500  -0.1076   0.01485   0.00929  -0.1263   0.7551   0.0068
  -6.250  -0.0851   0.01357   0.00784  -0.1254   0.7521   0.0065
  -6.000  -0.0617   0.01269   0.00685  -0.1248   0.7488   0.0063
  -5.750  -0.0375   0.01205   0.00613  -0.1243   0.7454   0.0063
  -5.500  -0.0130   0.01151   0.00551  -0.1239   0.7420   0.0062
  -5.250   0.0122   0.01107   0.00498  -0.1237   0.7385   0.0063
  -5.000   0.0378   0.01064   0.00452  -0.1234   0.7357   0.0064
  -4.750   0.0638   0.01027   0.00411  -0.1233   0.7326   0.0067
  -4.500   0.0902   0.00996   0.00376  -0.1232   0.7294   0.0069
  -4.250   0.1170   0.00970   0.00345  -0.1232   0.7262   0.0074
  -4.000   0.1440   0.00942   0.00310  -0.1232   0.7227   0.0085
  -3.750   0.1712   0.00918   0.00285  -0.1232   0.7200   0.0108
  -3.500   0.1980   0.00880   0.00259  -0.1233   0.7170   0.0332
  -3.250   0.2254   0.00856   0.00244  -0.1234   0.7138   0.0560
  -3.000   0.2528   0.00834   0.00232  -0.1237   0.7107   0.0878
  -2.750   0.2803   0.00807   0.00220  -0.1240   0.7073   0.1438
  -2.500   0.3070   0.00740   0.00206  -0.1246   0.7044   0.2961
  -2.250   0.3339   0.00623   0.00187  -0.1257   0.7013   0.5970
  -2.000   0.3624   0.00611   0.00191  -0.1259   0.6980   0.6704
  -1.750   0.3911   0.00614   0.00192  -0.1261   0.6947   0.6918
  -1.500   0.4199   0.00621   0.00195  -0.1264   0.6912   0.7075
  -1.250   0.4484   0.00624   0.00198  -0.1266   0.6881   0.7193
  -1.000   0.4772   0.00629   0.00200  -0.1268   0.6846   0.7288
  -0.750   0.5054   0.00632   0.00202  -0.1270   0.6810   0.7352
  -0.500   0.5339   0.00639   0.00205  -0.1271   0.6773   0.7417
  -0.250   0.5622   0.00647   0.00210  -0.1273   0.6735   0.7492
   0.000   0.5901   0.00653   0.00219  -0.1273   0.6698   0.7577
   0.250   0.6178   0.00660   0.00225  -0.1273   0.6658   0.7659
   0.500   0.6453   0.00669   0.00232  -0.1273   0.6617   0.7713
   0.750   0.6735   0.00674   0.00235  -0.1275   0.6575   0.7743
   1.000   0.7019   0.00676   0.00236  -0.1278   0.6533   0.7763
   1.250   0.7302   0.00680   0.00237  -0.1280   0.6487   0.7781
   1.500   0.7578   0.00685   0.00238  -0.1281   0.6438   0.7802
   1.750   0.7857   0.00684   0.00240  -0.1283   0.6392   0.7820
   2.000   0.8133   0.00687   0.00243  -0.1284   0.6339   0.7837
   2.250   0.8403   0.00695   0.00247  -0.1284   0.6287   0.7857
   2.500   0.8681   0.00698   0.00252  -0.1286   0.6235   0.7878
   2.750   0.8954   0.00703   0.00257  -0.1286   0.6174   0.7899
   3.000   0.9221   0.00711   0.00262  -0.1286   0.6117   0.7918
   3.250   0.9498   0.00716   0.00267  -0.1288   0.6054   0.7936
   3.500   0.9761   0.00725   0.00274  -0.1287   0.5985   0.7953
   3.750   1.0027   0.00729   0.00280  -0.1286   0.5914   0.7975
   4.000   1.0281   0.00738   0.00288  -0.1283   0.5832   0.7996
   4.250   1.0541   0.00746   0.00297  -0.1282   0.5750   0.8017
   4.750   1.1044   0.00768   0.00318  -0.1275   0.5565   0.8061
   5.000   1.1289   0.00782   0.00330  -0.1271   0.5464   0.8083
   5.250   1.1523   0.00799   0.00344  -0.1264   0.5351   0.8104
   5.500   1.1757   0.00814   0.00357  -0.1258   0.5220   0.8126
   5.750   1.1978   0.00831   0.00373  -0.1249   0.5078   0.8150
   6.000   1.2186   0.00853   0.00392  -0.1238   0.4924   0.8176
   6.250   1.2383   0.00878   0.00413  -0.1224   0.4759   0.8203
   6.750   1.2707   0.00936   0.00460  -0.1183   0.4395   0.8260
   7.000   1.2853   0.00971   0.00488  -0.1160   0.4192   0.8289
   7.250   1.2986   0.01011   0.00522  -0.1135   0.3988   0.8320
   7.500   1.3111   0.01056   0.00560  -0.1109   0.3784   0.8353
   7.750   1.3238   0.01103   0.00600  -0.1085   0.3572   0.8388
   8.000   1.3360   0.01154   0.00644  -0.1060   0.3374   0.8423
   8.500   1.3571   0.01265   0.00745  -0.1006   0.2982   0.8505
   8.750   1.3670   0.01329   0.00802  -0.0979   0.2786   0.8549
   9.000   1.3758   0.01401   0.00867  -0.0952   0.2594   0.8592
   9.250   1.3847   0.01471   0.00934  -0.0926   0.2429   0.8642
   9.500   1.3923   0.01554   0.01010  -0.0899   0.2243   0.8697
   9.750   1.4002   0.01641   0.01092  -0.0873   0.2064   0.8755
  10.000   1.4083   0.01727   0.01176  -0.0849   0.1914   0.8824
  10.250   1.4154   0.01824   0.01270  -0.0824   0.1754   0.8904
  10.500   1.4228   0.01919   0.01364  -0.0801   0.1623   0.9003
  10.750   1.4294   0.02017   0.01463  -0.0777   0.1502   0.9142
  11.000   1.4342   0.02112   0.01566  -0.0750   0.1384   0.9572
  11.250   1.4431   0.02233   0.01682  -0.0735   0.1255   1.0000
  11.500   1.4511   0.02360   0.01804  -0.0719   0.1136   1.0000
  11.750   1.4593   0.02488   0.01929  -0.0704   0.1027   1.0000
  12.000   1.4662   0.02628   0.02065  -0.0688   0.0917   1.0000
  12.250   1.4730   0.02774   0.02208  -0.0673   0.0818   1.0000
  12.500   1.4795   0.02924   0.02355  -0.0658   0.0725   1.0000
  12.750   1.4856   0.03082   0.02511  -0.0644   0.0643   1.0000
  13.000   1.4904   0.03255   0.02680  -0.0630   0.0562   1.0000
  13.250   1.4983   0.03409   0.02835  -0.0619   0.0508   1.0000
  13.500   1.5042   0.03582   0.03007  -0.0608   0.0448   1.0000
  13.750   1.5085   0.03773   0.03197  -0.0596   0.0391   1.0000
  14.000   1.5133   0.03965   0.03390  -0.0586   0.0340   1.0000
  14.250   1.5196   0.04149   0.03576  -0.0578   0.0302   1.0000
  14.500   1.5242   0.04354   0.03782  -0.0569   0.0268   1.0000
  14.750   1.5300   0.04551   0.03982  -0.0562   0.0242   1.0000
  15.000   1.5347   0.04765   0.04200  -0.0556   0.0218   1.0000
  15.250   1.5392   0.04986   0.04425  -0.0550   0.0196   1.0000
  15.500   1.5438   0.05211   0.04654  -0.0545   0.0178   1.0000
  15.750   1.5475   0.05451   0.04898  -0.0541   0.0160   1.0000
  16.000   1.5513   0.05693   0.05145  -0.0538   0.0146   1.0000
  16.250   1.5549   0.05945   0.05403  -0.0536   0.0133   1.0000
  16.500   1.5560   0.06233   0.05696  -0.0535   0.0121   1.0000
  16.750   1.5604   0.06485   0.05955  -0.0535   0.0111   1.0000
  17.000   1.5610   0.06789   0.06264  -0.0536   0.0101   1.0000
  17.250   1.5626   0.07087   0.06570  -0.0538   0.0092   1.0000
  17.500   1.5641   0.07392   0.06883  -0.0541   0.0086   1.0000
  17.750   1.5627   0.07742   0.07238  -0.0545   0.0076   1.0000
  18.000   1.5631   0.08075   0.07580  -0.0551   0.0071   1.0000
  18.250   1.5625   0.08426   0.07939  -0.0558   0.0065   1.0000
  18.500   1.5598   0.08812   0.08333  -0.0566   0.0059   1.0000
  18.750   1.5575   0.09201   0.08731  -0.0575   0.0055   1.0000
  19.000   1.5555   0.09592   0.09130  -0.0586   0.0051   1.0000
  19.250   1.5518   0.10014   0.09561  -0.0599   0.0046   1.0000
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