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EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 556 AIRFOIL (e556-il)
Reynolds number: 500,000
Max Cl/Cd: 97.95 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e556-il-500000.txt
Download as CSV file: xf-e556-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 556 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.5339   0.13134   0.12880  -0.0378   1.0000   0.0106
 -15.250  -0.5621   0.11972   0.11713  -0.0426   1.0000   0.0101
 -15.000  -0.6138   0.10287   0.10009  -0.0514   1.0000   0.0098
 -14.750  -0.6417   0.09298   0.09004  -0.0568   1.0000   0.0096
 -14.500  -0.6718   0.08356   0.08044  -0.0620   1.0000   0.0095
 -14.250  -0.6930   0.07649   0.07320  -0.0657   1.0000   0.0093
 -14.000  -0.7172   0.06946   0.06598  -0.0691   1.0000   0.0092
 -13.750  -0.7375   0.06358   0.05989  -0.0716   1.0000   0.0091
 -13.500  -0.7567   0.05835   0.05444  -0.0733   1.0000   0.0089
 -13.250  -0.7720   0.05398   0.04987  -0.0743   1.0000   0.0087
 -13.000  -0.7794   0.05082   0.04660  -0.0746   1.0000   0.0089
 -12.750  -0.7888   0.04753   0.04314  -0.0744   1.0000   0.0088
 -12.500  -0.7943   0.04489   0.04039  -0.0739   1.0000   0.0088
 -12.250  -0.7981   0.04260   0.03798  -0.0730   1.0000   0.0088
 -12.000  -0.8020   0.04050   0.03577  -0.0717   1.0000   0.0087
 -11.750  -0.8064   0.03861   0.03382  -0.0702   1.0000   0.0089
 -11.500  -0.8120   0.03690   0.03203  -0.0680   1.0000   0.0089
 -11.250  -0.8196   0.03540   0.03047  -0.0654   1.0000   0.0089
 -11.000  -0.8322   0.03400   0.02902  -0.0620   1.0000   0.0089
 -10.750  -0.8106   0.03206   0.02697  -0.0649   0.9969   0.0092
 -10.500  -0.7864   0.03026   0.02506  -0.0680   0.9934   0.0093
 -10.250  -0.7644   0.02846   0.02317  -0.0707   0.9881   0.0097
 -10.000  -0.7342   0.02665   0.02126  -0.0748   0.9849   0.0099
  -9.750  -0.7085   0.02485   0.01935  -0.0778   0.9789   0.0102
  -9.500  -0.6765   0.02273   0.01712  -0.0825   0.9750   0.0107
  -9.250  -0.6504   0.02096   0.01529  -0.0854   0.9689   0.0112
  -9.000  -0.6181   0.01975   0.01405  -0.0882   0.9650   0.0120
  -8.750  -0.5824   0.01870   0.01290  -0.0914   0.9627   0.0131
  -8.500  -0.5552   0.01736   0.01152  -0.0932   0.9566   0.0144
  -8.250  -0.5214   0.01649   0.01060  -0.0955   0.9529   0.0161
  -8.000  -0.4854   0.01545   0.00953  -0.0983   0.9505   0.0193
  -7.750  -0.4481   0.01454   0.00861  -0.1012   0.9487   0.0259
  -7.500  -0.4201   0.01367   0.00777  -0.1022   0.9419   0.0348
  -7.250  -0.3841   0.01291   0.00705  -0.1046   0.9383   0.0477
  -7.000  -0.3451   0.01207   0.00631  -0.1078   0.9357   0.0699
  -6.750  -0.3064   0.01119   0.00559  -0.1110   0.9319   0.1083
  -6.500  -0.2718   0.01009   0.00481  -0.1137   0.9250   0.1793
  -6.250  -0.2299   0.00863   0.00399  -0.1184   0.9208   0.3354
  -6.000  -0.1939   0.00846   0.00386  -0.1203   0.9131   0.3720
  -5.750  -0.1548   0.00839   0.00372  -0.1226   0.9059   0.3905
  -5.500  -0.1205   0.00837   0.00364  -0.1238   0.8964   0.4025
  -5.000  -0.0528   0.00845   0.00352  -0.1261   0.8764   0.4233
  -4.750  -0.0218   0.00849   0.00349  -0.1267   0.8656   0.4310
  -4.500   0.0098   0.00855   0.00344  -0.1273   0.8552   0.4374
  -4.250   0.0388   0.00859   0.00338  -0.1274   0.8437   0.4436
  -4.000   0.0674   0.00873   0.00350  -0.1274   0.8325   0.4522
  -3.750   0.0966   0.00883   0.00349  -0.1276   0.8218   0.4593
  -3.500   0.1249   0.00881   0.00342  -0.1276   0.8108   0.4623
  -3.250   0.1527   0.00880   0.00335  -0.1275   0.7997   0.4652
  -3.000   0.1810   0.00881   0.00328  -0.1275   0.7893   0.4681
  -2.750   0.2092   0.00882   0.00319  -0.1275   0.7786   0.4710
  -2.500   0.2369   0.00884   0.00311  -0.1274   0.7675   0.4738
  -2.250   0.2645   0.00878   0.00303  -0.1273   0.7572   0.4765
  -2.000   0.2922   0.00879   0.00298  -0.1272   0.7468   0.4790
  -1.750   0.3197   0.00880   0.00295  -0.1271   0.7361   0.4817
  -1.500   0.3474   0.00883   0.00292  -0.1270   0.7262   0.4848
  -1.250   0.3752   0.00888   0.00289  -0.1269   0.7159   0.4879
  -1.000   0.4027   0.00888   0.00285  -0.1269   0.7057   0.4907
  -0.750   0.4301   0.00889   0.00282  -0.1267   0.6961   0.4933
  -0.500   0.4574   0.00891   0.00283  -0.1266   0.6858   0.4961
  -0.250   0.4849   0.00895   0.00284  -0.1265   0.6760   0.4991
   0.250   0.5398   0.00907   0.00286  -0.1262   0.6560   0.5055
   0.500   0.5669   0.00908   0.00286  -0.1261   0.6465   0.5086
   0.750   0.5939   0.00913   0.00289  -0.1259   0.6365   0.5115
   1.000   0.6211   0.00918   0.00294  -0.1257   0.6264   0.5147
   1.250   0.6482   0.00927   0.00298  -0.1255   0.6168   0.5180
   1.500   0.6752   0.00935   0.00302  -0.1253   0.6064   0.5214
   1.750   0.7021   0.00939   0.00308  -0.1251   0.5966   0.5250
   2.000   0.7286   0.00948   0.00315  -0.1248   0.5867   0.5284
   2.250   0.7553   0.00955   0.00323  -0.1246   0.5760   0.5321
   2.500   0.7820   0.00965   0.00331  -0.1243   0.5656   0.5358
   2.750   0.8081   0.00977   0.00338  -0.1240   0.5551   0.5394
   3.000   0.8344   0.00983   0.00348  -0.1237   0.5439   0.5431
   3.250   0.8606   0.00993   0.00360  -0.1233   0.5332   0.5473
   3.500   0.8864   0.01008   0.00371  -0.1229   0.5227   0.5519
   3.750   0.9124   0.01018   0.00382  -0.1226   0.5116   0.5561
   4.000   0.9382   0.01029   0.00396  -0.1222   0.5006   0.5603
   4.250   0.9636   0.01044   0.00411  -0.1217   0.4896   0.5650
   4.500   0.9887   0.01061   0.00425  -0.1212   0.4779   0.5699
   4.750   1.0141   0.01072   0.00441  -0.1208   0.4661   0.5748
   5.000   1.0391   0.01088   0.00459  -0.1203   0.4545   0.5804
   5.250   1.0637   0.01108   0.00476  -0.1197   0.4430   0.5863
   5.500   1.0877   0.01126   0.00496  -0.1190   0.4306   0.5918
   5.750   1.1123   0.01143   0.00517  -0.1184   0.4181   0.5982
   6.000   1.1363   0.01163   0.00538  -0.1177   0.4054   0.6047
   6.250   1.1597   0.01184   0.00562  -0.1170   0.3922   0.6116
   6.500   1.1826   0.01209   0.00587  -0.1161   0.3783   0.6196
   6.750   1.2050   0.01234   0.00614  -0.1152   0.3642   0.6275
   7.000   1.2270   0.01263   0.00642  -0.1142   0.3496   0.6364
   7.250   1.2483   0.01292   0.00673  -0.1130   0.3337   0.6455
   7.500   1.2689   0.01324   0.00706  -0.1118   0.3169   0.6553
   8.000   1.3055   0.01399   0.00779  -0.1086   0.2797   0.6789
   8.250   1.3210   0.01446   0.00822  -0.1065   0.2596   0.6922
   8.500   1.3363   0.01496   0.00870  -0.1044   0.2383   0.7072
   8.750   1.3505   0.01552   0.00924  -0.1022   0.2186   0.7240
   9.000   1.3640   0.01612   0.00982  -0.0999   0.2005   0.7437
   9.250   1.3772   0.01670   0.01042  -0.0976   0.1833   0.7673
   9.500   1.3892   0.01730   0.01106  -0.0951   0.1675   0.7987
   9.750   1.3985   0.01786   0.01172  -0.0921   0.1534   0.8483
  10.000   1.4025   0.01831   0.01230  -0.0881   0.1412   1.0000
  10.250   1.4137   0.01915   0.01308  -0.0860   0.1282   1.0000
  10.750   1.4345   0.02097   0.01481  -0.0816   0.1053   1.0000
  11.000   1.4447   0.02193   0.01576  -0.0796   0.0960   1.0000
  11.250   1.4532   0.02302   0.01683  -0.0775   0.0875   1.0000
  11.500   1.4606   0.02421   0.01802  -0.0754   0.0795   1.0000
  11.750   1.4693   0.02538   0.01921  -0.0735   0.0726   1.0000
  12.000   1.4742   0.02685   0.02066  -0.0715   0.0660   1.0000
  12.250   1.4821   0.02818   0.02202  -0.0699   0.0605   1.0000
  12.500   1.4858   0.02988   0.02373  -0.0681   0.0551   1.0000
  12.750   1.4923   0.03143   0.02533  -0.0666   0.0508   1.0000
  13.000   1.4923   0.03359   0.02749  -0.0650   0.0462   1.0000
  13.250   1.4996   0.03522   0.02920  -0.0639   0.0430   1.0000
  13.500   1.5012   0.03743   0.03143  -0.0627   0.0398   1.0000
  13.750   1.5020   0.03980   0.03387  -0.0617   0.0370   1.0000
  14.000   1.5058   0.04198   0.03613  -0.0609   0.0346   1.0000
  14.250   1.5054   0.04467   0.03886  -0.0603   0.0325   1.0000
  14.500   1.5017   0.04784   0.04209  -0.0597   0.0304   1.0000
  14.750   1.5053   0.05030   0.04466  -0.0595   0.0288   1.0000
  15.000   1.5053   0.05327   0.04770  -0.0594   0.0271   1.0000
  15.250   1.5007   0.05690   0.05139  -0.0595   0.0256   1.0000
  15.500   1.4958   0.06071   0.05528  -0.0598   0.0244   1.0000
  15.750   1.4980   0.06371   0.05840  -0.0601   0.0231   1.0000
  16.000   1.4969   0.06725   0.06201  -0.0607   0.0218   1.0000
  16.250   1.4916   0.07144   0.06628  -0.0616   0.0209   1.0000
  16.500   1.4800   0.07671   0.07165  -0.0630   0.0199   1.0000
  16.750   1.4794   0.08048   0.07554  -0.0640   0.0191   1.0000
  17.000   1.4776   0.08450   0.07966  -0.0652   0.0182   1.0000
  17.250   1.4735   0.08895   0.08421  -0.0667   0.0175   1.0000
  17.500   1.4669   0.09390   0.08925  -0.0685   0.0168   1.0000
  17.750   1.4572   0.09946   0.09490  -0.0706   0.0162   1.0000
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