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EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 654 AIRFOIL (e654-il)
Reynolds number: 200,000
Max Cl/Cd: 71.42 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e654-il-200000-n5.txt
Download as CSV file: xf-e654-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 654 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2254   0.05916   0.05414  -0.1343   0.7789   0.0113
 -11.500  -0.2706   0.04925   0.04388  -0.1414   0.7749   0.0111
 -11.250  -0.2955   0.04415   0.03850  -0.1436   0.7710   0.0111
 -11.000  -0.3107   0.04065   0.03479  -0.1441   0.7668   0.0111
 -10.750  -0.3238   0.03755   0.03142  -0.1436   0.7626   0.0109
 -10.500  -0.3274   0.03561   0.02930  -0.1426   0.7587   0.0111
 -10.250  -0.3313   0.03361   0.02706  -0.1411   0.7553   0.0112
 -10.000  -0.3335   0.03205   0.02531  -0.1390   0.7519   0.0113
  -9.750  -0.3312   0.03059   0.02365  -0.1372   0.7484   0.0115
  -9.500  -0.3227   0.02918   0.02203  -0.1358   0.7454   0.0116
  -9.250  -0.3115   0.02779   0.02042  -0.1345   0.7426   0.0120
  -9.000  -0.2972   0.02656   0.01897  -0.1335   0.7402   0.0123
  -8.750  -0.2810   0.02538   0.01756  -0.1326   0.7379   0.0126
  -8.500  -0.2636   0.02431   0.01632  -0.1317   0.7356   0.0131
  -8.250  -0.2457   0.02349   0.01545  -0.1309   0.7328   0.0134
  -8.000  -0.2264   0.02276   0.01466  -0.1302   0.7300   0.0139
  -7.750  -0.2061   0.02206   0.01386  -0.1296   0.7274   0.0147
  -7.500  -0.1848   0.02140   0.01305  -0.1291   0.7252   0.0158
  -7.250  -0.1630   0.02082   0.01245  -0.1287   0.7231   0.0170
  -7.000  -0.1402   0.02029   0.01180  -0.1283   0.7213   0.0185
  -6.750  -0.1173   0.01971   0.01115  -0.1281   0.7195   0.0201
  -6.500  -0.0950   0.01918   0.01056  -0.1276   0.7171   0.0221
  -6.250  -0.0722   0.01869   0.01006  -0.1272   0.7145   0.0245
  -6.000  -0.0485   0.01824   0.00959  -0.1270   0.7121   0.0287
  -5.750  -0.0244   0.01778   0.00910  -0.1267   0.7100   0.0337
  -5.500   0.0004   0.01736   0.00866  -0.1266   0.7081   0.0408
  -5.250   0.0257   0.01697   0.00829  -0.1266   0.7062   0.0510
  -5.000   0.0517   0.01662   0.00794  -0.1267   0.7045   0.0655
  -4.750   0.0780   0.01624   0.00761  -0.1269   0.7028   0.0853
  -4.500   0.1034   0.01590   0.00737  -0.1270   0.7007   0.1123
  -4.250   0.1285   0.01556   0.00718  -0.1270   0.6984   0.1469
  -4.000   0.1542   0.01522   0.00701  -0.1272   0.6963   0.1901
  -3.750   0.1805   0.01488   0.00684  -0.1276   0.6942   0.2432
  -3.500   0.2072   0.01449   0.00669  -0.1280   0.6922   0.3098
  -3.250   0.2345   0.01408   0.00655  -0.1285   0.6902   0.3901
  -3.000   0.2619   0.01373   0.00649  -0.1288   0.6883   0.4763
  -2.750   0.2889   0.01360   0.00661  -0.1287   0.6867   0.5526
  -2.500   0.3165   0.01368   0.00676  -0.1285   0.6853   0.6031
  -2.250   0.3426   0.01384   0.00695  -0.1282   0.6833   0.6349
  -2.000   0.3685   0.01401   0.00713  -0.1278   0.6809   0.6564
  -1.750   0.3951   0.01417   0.00725  -0.1276   0.6785   0.6727
  -1.500   0.4224   0.01431   0.00735  -0.1275   0.6762   0.6870
  -1.250   0.4501   0.01446   0.00744  -0.1275   0.6743   0.7001
  -1.000   0.4771   0.01460   0.00756  -0.1272   0.6725   0.7100
  -0.750   0.5062   0.01471   0.00758  -0.1276   0.6707   0.7208
  -0.500   0.5337   0.01484   0.00767  -0.1274   0.6691   0.7286
  -0.250   0.5617   0.01499   0.00777  -0.1276   0.6671   0.7380
   0.000   0.5846   0.01519   0.00803  -0.1267   0.6644   0.7439
   0.250   0.6101   0.01535   0.00818  -0.1264   0.6616   0.7509
   0.500   0.6370   0.01546   0.00827  -0.1264   0.6591   0.7573
   0.750   0.6633   0.01556   0.00837  -0.1262   0.6568   0.7622
   1.000   0.6917   0.01562   0.00839  -0.1264   0.6548   0.7678
   1.250   0.7222   0.01566   0.00837  -0.1271   0.6529   0.7733
   1.500   0.7489   0.01575   0.00846  -0.1270   0.6508   0.7768
   1.750   0.7706   0.01595   0.00873  -0.1261   0.6471   0.7810
   2.000   0.7959   0.01608   0.00887  -0.1259   0.6438   0.7855
   2.250   0.8242   0.01615   0.00893  -0.1263   0.6409   0.7901
   2.500   0.8515   0.01616   0.00894  -0.1263   0.6383   0.7930
   2.750   0.8807   0.01615   0.00891  -0.1267   0.6361   0.7964
   3.000   0.9050   0.01629   0.00909  -0.1263   0.6328   0.8003
   3.250   0.9277   0.01647   0.00934  -0.1257   0.6285   0.8044
   3.500   0.9538   0.01652   0.00941  -0.1257   0.6248   0.8081
   3.750   0.9811   0.01650   0.00940  -0.1256   0.6218   0.8111
   4.000   1.0111   0.01643   0.00931  -0.1262   0.6192   0.8143
   4.250   1.0292   0.01669   0.00969  -0.1248   0.6140   0.8184
   4.500   1.0534   0.01678   0.00983  -0.1244   0.6094   0.8227
   4.750   1.0801   0.01674   0.00981  -0.1243   0.6057   0.8259
   5.000   1.1071   0.01671   0.00980  -0.1243   0.6022   0.8290
   5.250   1.1227   0.01697   0.01018  -0.1224   0.5960   0.8333
   5.500   1.1470   0.01699   0.01024  -0.1220   0.5910   0.8378
   5.750   1.1755   0.01690   0.01016  -0.1223   0.5870   0.8416
   6.000   1.1867   0.01720   0.01060  -0.1196   0.5797   0.8460
   6.250   1.2097   0.01719   0.01062  -0.1189   0.5741   0.8503
   6.500   1.2274   0.01736   0.01088  -0.1174   0.5672   0.8554
   6.750   1.2415   0.01746   0.01104  -0.1151   0.5598   0.8605
   7.000   1.2562   0.01761   0.01125  -0.1130   0.5524   0.8666
   7.250   1.2713   0.01780   0.01149  -0.1110   0.5436   0.8731
   7.500   1.2815   0.01811   0.01188  -0.1083   0.5345   0.8797
   7.750   1.2993   0.01826   0.01203  -0.1068   0.5250   0.8868
   8.000   1.3059   0.01874   0.01259  -0.1037   0.5138   0.8960
   8.250   1.3154   0.01919   0.01308  -0.1012   0.5020   0.9076
   8.500   1.3246   0.01963   0.01356  -0.0986   0.4894   0.9239
   9.000   1.3451   0.02090   0.01481  -0.0948   0.4595   1.0000
   9.250   1.3554   0.02186   0.01571  -0.0932   0.4428   1.0000
   9.500   1.3636   0.02296   0.01675  -0.0915   0.4257   1.0000
   9.750   1.3704   0.02419   0.01793  -0.0898   0.4087   1.0000
  10.000   1.3763   0.02554   0.01921  -0.0880   0.3922   1.0000
  10.250   1.3812   0.02699   0.02061  -0.0862   0.3762   1.0000
  10.500   1.3856   0.02853   0.02211  -0.0845   0.3604   1.0000
  10.750   1.3893   0.03015   0.02368  -0.0828   0.3448   1.0000
  11.000   1.3932   0.03182   0.02531  -0.0812   0.3300   1.0000
  11.250   1.3965   0.03358   0.02704  -0.0797   0.3155   1.0000
  11.500   1.3997   0.03540   0.02882  -0.0783   0.3015   1.0000
  11.750   1.4033   0.03725   0.03066  -0.0769   0.2878   1.0000
  12.000   1.4074   0.03913   0.03253  -0.0758   0.2742   1.0000
  12.250   1.4116   0.04106   0.03445  -0.0747   0.2611   1.0000
  12.500   1.4157   0.04305   0.03643  -0.0736   0.2485   1.0000
  12.750   1.4189   0.04517   0.03853  -0.0727   0.2360   1.0000
  13.000   1.4219   0.04735   0.04070  -0.0717   0.2243   1.0000
  13.250   1.4262   0.04950   0.04285  -0.0710   0.2124   1.0000
  13.500   1.4308   0.05165   0.04501  -0.0703   0.2013   1.0000
  13.750   1.4340   0.05400   0.04737  -0.0697   0.1906   1.0000
  14.250   1.4409   0.05878   0.05218  -0.0686   0.1700   1.0000
  14.500   1.4443   0.06125   0.05467  -0.0682   0.1606   1.0000
  15.000   1.4503   0.06644   0.05990  -0.0677   0.1428   1.0000
  15.250   1.4523   0.06922   0.06271  -0.0675   0.1350   1.0000
  15.500   1.4543   0.07204   0.06556  -0.0674   0.1267   1.0000
  15.750   1.4570   0.07484   0.06842  -0.0674   0.1193   1.0000
  16.000   1.4570   0.07802   0.07162  -0.0675   0.1123   1.0000
  16.250   1.4602   0.08086   0.07453  -0.0676   0.1054   1.0000
  16.500   1.4588   0.08431   0.07800  -0.0679   0.0993   1.0000
  16.750   1.4619   0.08724   0.08101  -0.0682   0.0932   1.0000
  17.000   1.4597   0.09092   0.08473  -0.0687   0.0879   1.0000
  17.250   1.4623   0.09399   0.08789  -0.0692   0.0826   1.0000
  17.500   1.4599   0.09780   0.09175  -0.0699   0.0779   1.0000
  17.750   1.4611   0.10111   0.09516  -0.0706   0.0734   1.0000
  18.000   1.4594   0.10489   0.09900  -0.0715   0.0691   1.0000
  18.250   1.4583   0.10862   0.10282  -0.0725   0.0654   1.0000
  18.500   1.4574   0.11235   0.10663  -0.0736   0.0616   1.0000
  18.750   1.4535   0.11658   0.11090  -0.0749   0.0584   1.0000
  19.000   1.4538   0.12017   0.11461  -0.0761   0.0550   1.0000
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