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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 50,000
Max Cl/Cd: 37.02 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe613-il-50000-n5.txt
Download as CSV file: xf-goe613-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3507   0.10192   0.09559  -0.0304   1.0000   0.1267
  -7.750  -0.3770   0.10155   0.09539  -0.0291   1.0000   0.1283
  -7.500  -0.4019   0.10066   0.09465  -0.0300   1.0000   0.1291
  -7.250  -0.3876   0.09595   0.08998  -0.0258   1.0000   0.1319
  -7.000  -0.3876   0.09332   0.08741  -0.0236   1.0000   0.1352
  -6.750  -0.3957   0.09121   0.08534  -0.0226   1.0000   0.1395
  -6.500  -0.4189   0.08996   0.08417  -0.0262   1.0000   0.1444
  -6.250  -0.4128   0.08623   0.08051  -0.0221   1.0000   0.1481
  -6.000  -0.4140   0.08392   0.07823  -0.0206   1.0000   0.1558
  -5.750  -0.4198   0.08112   0.07545  -0.0214   1.0000   0.1628
  -5.500  -0.4171   0.07861   0.07297  -0.0193   1.0000   0.1696
  -5.000  -0.3618   0.06296   0.05608  -0.0390   0.9917   0.0841
  -4.750  -0.3347   0.05882   0.05186  -0.0415   0.9858   0.0828
  -4.500  -0.3039   0.05476   0.04739  -0.0453   0.9781   0.0831
  -4.250  -0.2741   0.05112   0.04350  -0.0480   0.9708   0.0816
  -4.000  -0.2406   0.04760   0.03961  -0.0511   0.9641   0.0796
  -3.750  -0.2114   0.04462   0.03619  -0.0529   0.9562   0.0782
  -3.500  -0.1764   0.04196   0.03304  -0.0554   0.9502   0.0787
  -3.250  -0.1478   0.03994   0.03055  -0.0563   0.9422   0.0809
  -3.000  -0.1107   0.03787   0.02796  -0.0585   0.9366   0.0813
  -2.750  -0.0832   0.03622   0.02593  -0.0587   0.9280   0.0811
  -2.500  -0.0453   0.03460   0.02390  -0.0606   0.9221   0.0812
  -2.250  -0.0169   0.03339   0.02237  -0.0608   0.9133   0.0816
  -2.000   0.0220   0.03219   0.02082  -0.0626   0.9072   0.0824
  -1.750   0.0505   0.03132   0.01971  -0.0627   0.8976   0.0851
  -1.500   0.0909   0.03035   0.01868  -0.0651   0.8915   0.0898
  -1.250   0.1198   0.02968   0.01787  -0.0650   0.8810   0.0925
  -1.000   0.1563   0.02900   0.01699  -0.0662   0.8724   0.0950
  -0.750   0.1944   0.02835   0.01616  -0.0676   0.8635   0.0980
  -0.500   0.2252   0.02772   0.01550  -0.0679   0.8518   0.1021
  -0.250   0.2589   0.02714   0.01484  -0.0686   0.8403   0.1097
   0.000   0.2971   0.02642   0.01412  -0.0700   0.8300   0.1273
   0.250   0.3337   0.02551   0.01344  -0.0712   0.8188   0.1640
   0.500   0.3920   0.02288   0.01302  -0.0763   0.8083   1.0000
   0.750   0.4231   0.02275   0.01260  -0.0762   0.7946   1.0000
   1.000   0.4541   0.02262   0.01224  -0.0762   0.7808   1.0000
   1.250   0.4850   0.02248   0.01190  -0.0761   0.7667   1.0000
   1.500   0.5155   0.02234   0.01160  -0.0760   0.7519   1.0000
   1.750   0.5456   0.02221   0.01133  -0.0758   0.7365   1.0000
   2.000   0.5752   0.02211   0.01111  -0.0755   0.7202   1.0000
   2.250   0.6044   0.02204   0.01092  -0.0751   0.7031   1.0000
   2.500   0.6334   0.02198   0.01074  -0.0747   0.6853   1.0000
   2.750   0.6608   0.02199   0.01066  -0.0741   0.6667   1.0000
   3.000   0.6841   0.02213   0.01072  -0.0729   0.6456   1.0000
   3.250   0.7107   0.02220   0.01068  -0.0722   0.6257   1.0000
   3.500   0.7364   0.02232   0.01071  -0.0714   0.6054   1.0000
   3.750   0.7616   0.02251   0.01080  -0.0706   0.5854   1.0000
   4.000   0.7884   0.02270   0.01088  -0.0700   0.5664   1.0000
   4.250   0.8147   0.02297   0.01101  -0.0694   0.5483   1.0000
   4.500   0.8389   0.02337   0.01132  -0.0686   0.5302   1.0000
   4.750   0.8631   0.02381   0.01169  -0.0678   0.5132   1.0000
   5.000   0.8872   0.02430   0.01215  -0.0671   0.4972   1.0000
   5.250   0.9111   0.02484   0.01266  -0.0664   0.4823   1.0000
   5.500   0.9349   0.02539   0.01320  -0.0657   0.4681   1.0000
   5.750   0.9591   0.02596   0.01379  -0.0652   0.4552   1.0000
   6.000   0.9829   0.02655   0.01439  -0.0645   0.4429   1.0000
   6.250   1.0043   0.02721   0.01514  -0.0636   0.4310   1.0000
   6.500   1.0265   0.02787   0.01588  -0.0628   0.4199   1.0000
   6.750   1.0503   0.02851   0.01658  -0.0622   0.4099   1.0000
   7.000   1.0721   0.02921   0.01739  -0.0613   0.3999   1.0000
   7.250   1.0929   0.02998   0.01829  -0.0604   0.3902   1.0000
   7.500   1.1168   0.03063   0.01899  -0.0598   0.3813   1.0000
   7.750   1.1354   0.03147   0.02005  -0.0585   0.3717   1.0000
   8.000   1.1557   0.03227   0.02098  -0.0575   0.3628   1.0000
   8.250   1.1774   0.03300   0.02181  -0.0566   0.3540   1.0000
   8.500   1.1932   0.03396   0.02300  -0.0551   0.3449   1.0000
   8.750   1.2090   0.03460   0.02378  -0.0533   0.3334   1.0000
   9.000   1.2190   0.03512   0.02436  -0.0506   0.3192   1.0000
   9.250   1.2262   0.03567   0.02497  -0.0476   0.3048   1.0000
   9.500   1.2372   0.03631   0.02570  -0.0452   0.2934   1.0000
   9.750   1.2418   0.03728   0.02691  -0.0422   0.2828   1.0000
  10.000   1.2430   0.03809   0.02785  -0.0386   0.2709   1.0000
  10.250   1.2429   0.03897   0.02882  -0.0351   0.2587   1.0000
  10.500   1.2470   0.03996   0.02996  -0.0324   0.2489   1.0000
  10.750   1.2487   0.04134   0.03166  -0.0298   0.2397   1.0000
  11.000   1.2480   0.04271   0.03318  -0.0272   0.2290   1.0000
  11.250   1.2432   0.04438   0.03498  -0.0246   0.2161   1.0000
  11.500   1.2391   0.04632   0.03708  -0.0226   0.2033   1.0000
  11.750   1.2318   0.04882   0.03978  -0.0210   0.1870   1.0000
  12.000   1.2240   0.05170   0.04285  -0.0199   0.1688   1.0000
  12.250   1.2138   0.05507   0.04627  -0.0193   0.1460   1.0000
  12.500   1.2011   0.05901   0.05013  -0.0191   0.1231   1.0000
  12.750   1.1865   0.06361   0.05468  -0.0195   0.1019   1.0000
  13.000   1.1697   0.06890   0.05994  -0.0205   0.0813   1.0000
  13.250   1.1526   0.07461   0.06564  -0.0221   0.0694   1.0000
  13.500   1.1350   0.08073   0.07177  -0.0240   0.0624   1.0000
  13.750   1.1201   0.08668   0.07779  -0.0260   0.0585   1.0000
  14.000   1.1053   0.09278   0.08395  -0.0282   0.0549   1.0000
  14.250   1.0911   0.09892   0.09013  -0.0305   0.0520   1.0000
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