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GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 508 AIRFOIL (goe508-il)
Reynolds number: 500,000
Max Cl/Cd: 105.71 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe508-il-500000.txt
Download as CSV file: xf-goe508-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 508 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1073   0.05680   0.05345  -0.1370   0.8253   0.0422
 -10.250  -0.3549   0.03155   0.02711  -0.1376   0.8061   0.0388
 -10.000  -0.3586   0.02943   0.02474  -0.1346   0.7993   0.0390
  -9.750  -0.3500   0.02809   0.02322  -0.1326   0.7933   0.0393
  -9.500  -0.3432   0.02638   0.02125  -0.1303   0.7877   0.0395
  -9.250  -0.3313   0.02505   0.01974  -0.1284   0.7821   0.0398
  -9.000  -0.3175   0.02378   0.01825  -0.1267   0.7768   0.0401
  -8.750  -0.3006   0.02277   0.01702  -0.1253   0.7719   0.0406
  -8.500  -0.2831   0.02180   0.01587  -0.1238   0.7669   0.0412
  -8.250  -0.2646   0.02084   0.01471  -0.1225   0.7616   0.0416
  -8.000  -0.2444   0.02005   0.01371  -0.1212   0.7564   0.0419
  -7.750  -0.2226   0.01943   0.01287  -0.1202   0.7515   0.0422
  -7.500  -0.2018   0.01821   0.01158  -0.1192   0.7464   0.0428
  -7.250  -0.1786   0.01748   0.01082  -0.1185   0.7412   0.0433
  -7.000  -0.1545   0.01696   0.01024  -0.1178   0.7364   0.0439
  -6.750  -0.1300   0.01651   0.00972  -0.1172   0.7316   0.0445
  -6.500  -0.1059   0.01604   0.00921  -0.1165   0.7264   0.0452
  -6.250  -0.0813   0.01561   0.00870  -0.1158   0.7211   0.0460
  -6.000  -0.0561   0.01525   0.00821  -0.1151   0.7160   0.0469
  -5.750  -0.0312   0.01493   0.00781  -0.1145   0.7106   0.0476
  -5.500  -0.0077   0.01423   0.00713  -0.1137   0.7050   0.0487
  -5.250   0.0173   0.01388   0.00675  -0.1131   0.6998   0.0497
  -5.000   0.0426   0.01359   0.00642  -0.1125   0.6947   0.0509
  -4.750   0.0676   0.01329   0.00610  -0.1118   0.6889   0.0521
  -4.500   0.0932   0.01307   0.00580  -0.1112   0.6835   0.0532
  -4.250   0.1171   0.01262   0.00533  -0.1104   0.6783   0.0549
  -4.000   0.1418   0.01236   0.00510  -0.1097   0.6725   0.0567
  -3.750   0.1672   0.01217   0.00487  -0.1091   0.6666   0.0589
  -3.500   0.1919   0.01190   0.00455  -0.1084   0.6612   0.0613
  -3.250   0.2169   0.01169   0.00437  -0.1077   0.6557   0.0642
  -3.000   0.2421   0.01149   0.00416  -0.1071   0.6501   0.0676
  -2.750   0.2677   0.01135   0.00399  -0.1065   0.6450   0.0721
  -2.500   0.2932   0.01120   0.00388  -0.1059   0.6398   0.0784
  -2.250   0.3186   0.01107   0.00380  -0.1053   0.6341   0.0878
  -2.000   0.3442   0.01098   0.00371  -0.1048   0.6283   0.1011
  -1.750   0.3698   0.01091   0.00364  -0.1042   0.6224   0.1146
  -1.500   0.3950   0.01080   0.00358  -0.1036   0.6164   0.1267
  -1.250   0.4206   0.01073   0.00351  -0.1031   0.6113   0.1375
  -1.000   0.4467   0.01071   0.00347  -0.1026   0.6066   0.1480
  -0.750   0.4719   0.01063   0.00344  -0.1020   0.6015   0.1601
  -0.500   0.4969   0.01055   0.00340  -0.1014   0.5962   0.1769
  -0.250   0.5220   0.01047   0.00338  -0.1008   0.5913   0.2045
   0.250   0.5684   0.01005   0.00340  -0.0991   0.5819   0.3393
   0.500   0.5868   0.00959   0.00343  -0.0973   0.5773   0.5043
   0.750   0.5996   0.00905   0.00352  -0.0942   0.5729   0.7164
   1.000   0.6410   0.00875   0.00379  -0.0965   0.5686   0.9129
   1.250   0.7118   0.00895   0.00396  -0.1053   0.5631   0.9572
   1.500   0.7546   0.00914   0.00405  -0.1083   0.5581   0.9722
   1.750   0.7970   0.00932   0.00416  -0.1113   0.5532   0.9822
   2.000   0.8416   0.00941   0.00423  -0.1148   0.5476   0.9892
   2.250   0.8844   0.00953   0.00428  -0.1180   0.5422   0.9949
   2.500   0.9340   0.00969   0.00433  -0.1227   0.5372   1.0000
   2.750   0.9532   0.00973   0.00439  -0.1210   0.5331   1.0000
   3.000   0.9726   0.00980   0.00445  -0.1194   0.5284   1.0000
   3.250   0.9920   0.00991   0.00450  -0.1178   0.5240   1.0000
   3.500   1.0120   0.01006   0.00459  -0.1163   0.5197   1.0000
   3.750   1.0311   0.01013   0.00469  -0.1146   0.5155   1.0000
   4.000   1.0503   0.01022   0.00478  -0.1129   0.5109   1.0000
   4.250   1.0693   0.01035   0.00487  -0.1112   0.5063   1.0000
   4.500   1.0884   0.01051   0.00498  -0.1095   0.5017   1.0000
   4.750   1.1070   0.01059   0.00510  -0.1077   0.4968   1.0000
   5.000   1.1251   0.01071   0.00521  -0.1058   0.4914   1.0000
   5.250   1.1425   0.01089   0.00533  -0.1038   0.4861   1.0000
   5.500   1.1601   0.01099   0.00547  -0.1018   0.4806   1.0000
   5.750   1.1765   0.01113   0.00561  -0.0996   0.4742   1.0000
   6.000   1.1908   0.01133   0.00576  -0.0970   0.4678   1.0000
   6.250   1.2030   0.01144   0.00590  -0.0939   0.4601   1.0000
   6.500   1.2116   0.01165   0.00606  -0.0902   0.4518   1.0000
   6.750   1.2236   0.01183   0.00626  -0.0873   0.4414   1.0000
   7.000   1.2338   0.01211   0.00650  -0.0841   0.4301   1.0000
   7.250   1.2424   0.01247   0.00681  -0.0807   0.4160   1.0000
   7.500   1.2492   0.01296   0.00723  -0.0773   0.3963   1.0000
   7.750   1.2512   0.01368   0.00783  -0.0732   0.3720   1.0000
   8.000   1.2520   0.01460   0.00862  -0.0693   0.3472   1.0000
   8.250   1.2519   0.01570   0.00958  -0.0656   0.3231   1.0000
   8.500   1.2527   0.01690   0.01065  -0.0623   0.3035   1.0000
   8.750   1.2580   0.01799   0.01166  -0.0597   0.2891   1.0000
   9.000   1.2676   0.01893   0.01257  -0.0578   0.2799   1.0000
   9.250   1.2751   0.02002   0.01362  -0.0557   0.2721   1.0000
   9.500   1.2874   0.02089   0.01449  -0.0543   0.2664   1.0000
   9.750   1.2983   0.02186   0.01546  -0.0528   0.2611   1.0000
  10.000   1.3063   0.02304   0.01660  -0.0511   0.2559   1.0000
  10.250   1.3195   0.02391   0.01751  -0.0499   0.2519   1.0000
  10.500   1.3322   0.02485   0.01847  -0.0488   0.2479   1.0000
  10.750   1.3429   0.02592   0.01954  -0.0475   0.2441   1.0000
  11.000   1.3514   0.02716   0.02077  -0.0461   0.2405   1.0000
  11.250   1.3630   0.02821   0.02185  -0.0450   0.2375   1.0000
  11.500   1.3770   0.02913   0.02282  -0.0441   0.2351   1.0000
  11.750   1.3900   0.03013   0.02386  -0.0432   0.2323   1.0000
  12.000   1.4014   0.03126   0.02501  -0.0422   0.2296   1.0000
  12.250   1.4112   0.03250   0.02627  -0.0412   0.2267   1.0000
  12.500   1.4194   0.03387   0.02762  -0.0400   0.2234   1.0000
  12.750   1.4320   0.03497   0.02878  -0.0393   0.2209   1.0000
  13.000   1.4449   0.03608   0.02996  -0.0387   0.2179   1.0000
  13.250   1.4557   0.03736   0.03129  -0.0379   0.2147   1.0000
  13.500   1.4643   0.03882   0.03275  -0.0371   0.2111   1.0000
  13.750   1.4702   0.04047   0.03437  -0.0361   0.2069   1.0000
  14.000   1.4831   0.04168   0.03568  -0.0357   0.2046   1.0000
  14.250   1.4943   0.04303   0.03711  -0.0352   0.2016   1.0000
  14.500   1.5037   0.04452   0.03864  -0.0346   0.1983   1.0000
  14.750   1.5105   0.04625   0.04037  -0.0339   0.1949   1.0000
  15.000   1.5168   0.04802   0.04216  -0.0333   0.1913   1.0000
  15.250   1.5284   0.04940   0.04364  -0.0330   0.1884   1.0000
  15.500   1.5370   0.05107   0.04538  -0.0326   0.1847   1.0000
  15.750   1.5432   0.05296   0.04729  -0.0321   0.1808   1.0000
  16.000   1.5470   0.05509   0.04943  -0.0317   0.1771   1.0000
  16.250   1.5569   0.05669   0.05111  -0.0314   0.1725   1.0000
  16.500   1.5616   0.05881   0.05328  -0.0311   0.1678   1.0000
  16.750   1.5639   0.06119   0.05567  -0.0308   0.1625   1.0000
  17.000   1.5698   0.06321   0.05775  -0.0306   0.1574   1.0000
  17.250   1.5694   0.06593   0.06046  -0.0304   0.1516   1.0000
  17.500   1.5729   0.06821   0.06279  -0.0302   0.1466   1.0000
  17.750   1.5714   0.07107   0.06567  -0.0300   0.1403   1.0000
  18.000   1.5715   0.07378   0.06841  -0.0299   0.1355   1.0000
  18.250   1.5690   0.07681   0.07145  -0.0298   0.1296   1.0000
  18.500   1.5657   0.07993   0.07460  -0.0298   0.1245   1.0000
  18.750   1.5646   0.08283   0.07754  -0.0298   0.1200   1.0000
  19.000   1.5573   0.08650   0.08122  -0.0300   0.1141   1.0000
  19.250   1.5544   0.08970   0.08446  -0.0302   0.1091   1.0000
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