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GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 758 AIRFOIL (goe758-il)
Reynolds number: 200,000
Max Cl/Cd: 75.58 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe758-il-200000-n5.txt
Download as CSV file: xf-goe758-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 758 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2682   0.11207   0.10849  -0.0460   1.0000   0.0403
 -10.750  -0.2868   0.10667   0.10316  -0.0507   1.0000   0.0420
 -10.500  -0.2882   0.10227   0.09881  -0.0530   0.9937   0.0421
 -10.000  -0.2531   0.09540   0.09192  -0.0569   0.9708   0.0434
  -9.750  -0.2539   0.08546   0.08193  -0.0656   0.9556   0.0350
  -9.500  -0.2347   0.08144   0.07787  -0.0702   0.9421   0.0344
  -9.250  -0.2191   0.07569   0.07207  -0.0774   0.9276   0.0338
  -9.000  -0.2080   0.06869   0.06501  -0.0862   0.9108   0.0333
  -8.750  -0.2119   0.05942   0.05567  -0.0970   0.8892   0.0332
  -8.500  -0.2516   0.04692   0.04280  -0.1084   0.8638   0.0327
  -8.250  -0.2652   0.04137   0.03683  -0.1095   0.8466   0.0326
  -8.000  -0.2667   0.03733   0.03235  -0.1092   0.8318   0.0327
  -7.750  -0.2612   0.03409   0.02869  -0.1083   0.8177   0.0328
  -7.500  -0.2506   0.03142   0.02562  -0.1073   0.8039   0.0329
  -7.250  -0.2365   0.02919   0.02300  -0.1062   0.7899   0.0331
  -7.000  -0.2196   0.02739   0.02080  -0.1052   0.7757   0.0336
  -6.750  -0.2006   0.02592   0.01894  -0.1042   0.7614   0.0342
  -6.500  -0.1801   0.02462   0.01728  -0.1033   0.7475   0.0347
  -6.250  -0.1585   0.02343   0.01577  -0.1024   0.7336   0.0348
  -6.000  -0.1359   0.02240   0.01443  -0.1016   0.7200   0.0350
  -5.750  -0.1124   0.02152   0.01328  -0.1009   0.7076   0.0352
  -5.500  -0.0883   0.02074   0.01226  -0.1002   0.6969   0.0354
  -5.000  -0.0397   0.01885   0.01011  -0.0991   0.6787   0.0361
  -4.750  -0.0150   0.01820   0.00936  -0.0987   0.6712   0.0369
  -4.500   0.0101   0.01765   0.00875  -0.0982   0.6639   0.0377
  -4.250   0.0354   0.01716   0.00816  -0.0977   0.6575   0.0383
  -4.000   0.0607   0.01669   0.00760  -0.0972   0.6515   0.0387
  -3.750   0.0861   0.01626   0.00711  -0.0968   0.6455   0.0391
  -3.500   0.1115   0.01589   0.00665  -0.0963   0.6403   0.0396
  -3.250   0.1370   0.01555   0.00625  -0.0958   0.6352   0.0401
  -3.000   0.1625   0.01525   0.00590  -0.0954   0.6297   0.0406
  -2.750   0.1883   0.01501   0.00557  -0.0950   0.6249   0.0412
  -2.500   0.2143   0.01480   0.00529  -0.0946   0.6203   0.0419
  -2.250   0.2401   0.01456   0.00502  -0.0942   0.6150   0.0429
  -2.000   0.2661   0.01437   0.00476  -0.0939   0.6102   0.0450
  -1.750   0.2927   0.01426   0.00456  -0.0936   0.6058   0.0470
  -1.500   0.3190   0.01413   0.00441  -0.0933   0.6005   0.0489
  -1.250   0.3453   0.01402   0.00427  -0.0929   0.5952   0.0518
  -1.000   0.3718   0.01391   0.00415  -0.0926   0.5907   0.0602
  -0.750   0.3967   0.01355   0.00407  -0.0922   0.5858   0.1347
  -0.500   0.4202   0.01302   0.00406  -0.0917   0.5807   0.2841
  -0.250   0.4441   0.01268   0.00409  -0.0912   0.5762   0.3969
   0.000   0.4674   0.01241   0.00418  -0.0903   0.5720   0.5196
   0.250   0.4910   0.01223   0.00427  -0.0894   0.5668   0.6008
   0.500   0.5154   0.01212   0.00431  -0.0885   0.5620   0.6582
   0.750   0.5389   0.01190   0.00434  -0.0873   0.5578   0.7453
   1.000   0.6215   0.01158   0.00441  -0.0984   0.5510   0.9971
   1.250   0.6483   0.01169   0.00444  -0.0983   0.5457   1.0000
   1.500   0.6729   0.01181   0.00444  -0.0976   0.5412   1.0000
   1.750   0.6971   0.01191   0.00452  -0.0969   0.5356   1.0000
   2.000   0.7215   0.01202   0.00458  -0.0963   0.5300   1.0000
   2.250   0.7462   0.01215   0.00461  -0.0956   0.5252   1.0000
   2.500   0.7707   0.01226   0.00472  -0.0950   0.5191   1.0000
   2.750   0.7952   0.01238   0.00480  -0.0944   0.5133   1.0000
   3.000   0.8198   0.01252   0.00487  -0.0937   0.5081   1.0000
   3.250   0.8441   0.01264   0.00501  -0.0931   0.5012   1.0000
   3.500   0.8685   0.01278   0.00510  -0.0925   0.4953   1.0000
   3.750   0.8929   0.01293   0.00523  -0.0918   0.4890   1.0000
   4.000   0.9170   0.01308   0.00537  -0.0912   0.4822   1.0000
   4.250   0.9410   0.01324   0.00550  -0.0905   0.4758   1.0000
   4.500   0.9648   0.01341   0.00567  -0.0898   0.4685   1.0000
   4.750   0.9885   0.01359   0.00581  -0.0890   0.4623   1.0000
   5.000   1.0121   0.01378   0.00603  -0.0883   0.4547   1.0000
   5.250   1.0352   0.01398   0.00619  -0.0875   0.4477   1.0000
   5.500   1.0584   0.01419   0.00644  -0.0867   0.4400   1.0000
   5.750   1.0811   0.01442   0.00665  -0.0859   0.4332   1.0000
   6.000   1.1038   0.01466   0.00691  -0.0851   0.4259   1.0000
   6.250   1.1255   0.01492   0.00715  -0.0841   0.4179   1.0000
   6.500   1.1473   0.01518   0.00743  -0.0831   0.4096   1.0000
   6.750   1.1682   0.01547   0.00770  -0.0820   0.4018   1.0000
   7.000   1.1893   0.01576   0.00803  -0.0809   0.3937   1.0000
   7.250   1.2095   0.01608   0.00835  -0.0797   0.3865   1.0000
   7.500   1.2301   0.01639   0.00870  -0.0786   0.3795   1.0000
   7.750   1.2495   0.01674   0.00906  -0.0773   0.3725   1.0000
   8.000   1.2690   0.01709   0.00946  -0.0761   0.3660   1.0000
   8.250   1.2875   0.01745   0.00986  -0.0747   0.3591   1.0000
   8.500   1.3049   0.01786   0.01028  -0.0731   0.3524   1.0000
   8.750   1.3193   0.01825   0.01071  -0.0710   0.3434   1.0000
   9.000   1.3323   0.01869   0.01118  -0.0687   0.3349   1.0000
   9.250   1.3437   0.01919   0.01168  -0.0662   0.3254   1.0000
   9.500   1.3564   0.01969   0.01224  -0.0640   0.3167   1.0000
   9.750   1.3665   0.02031   0.01285  -0.0616   0.3080   1.0000
  10.000   1.3782   0.02090   0.01352  -0.0595   0.2984   1.0000
  10.250   1.3881   0.02161   0.01426  -0.0573   0.2901   1.0000
  10.500   1.3972   0.02238   0.01508  -0.0551   0.2799   1.0000
  10.750   1.4050   0.02327   0.01602  -0.0530   0.2684   1.0000
  11.000   1.4111   0.02431   0.01708  -0.0508   0.2564   1.0000
  11.250   1.4138   0.02561   0.01839  -0.0485   0.2407   1.0000
  11.500   1.4155   0.02709   0.01986  -0.0463   0.2246   1.0000
  11.750   1.4124   0.02900   0.02172  -0.0441   0.2051   1.0000
  12.000   1.4054   0.03137   0.02401  -0.0420   0.1808   1.0000
  12.250   1.3927   0.03442   0.02692  -0.0399   0.1529   1.0000
  12.500   1.3741   0.03826   0.03059  -0.0382   0.1211   1.0000
  12.750   1.3537   0.04259   0.03476  -0.0369   0.0960   1.0000
  13.000   1.3422   0.04626   0.03840  -0.0362   0.0840   1.0000
  13.250   1.3329   0.04986   0.04201  -0.0356   0.0743   1.0000
  13.500   1.3282   0.05310   0.04529  -0.0353   0.0635   1.0000
  13.750   1.3198   0.05683   0.04903  -0.0352   0.0489   1.0000
  14.000   1.3069   0.06124   0.05340  -0.0353   0.0377   1.0000
  14.250   1.2977   0.06533   0.05752  -0.0355   0.0324   1.0000
  14.500   1.2898   0.06942   0.06166  -0.0358   0.0290   1.0000
  14.750   1.2835   0.07341   0.06573  -0.0363   0.0271   1.0000
  15.000   1.2768   0.07755   0.06996  -0.0369   0.0255   1.0000
  15.250   1.2724   0.08148   0.07400  -0.0376   0.0243   1.0000
  15.500   1.2668   0.08567   0.07828  -0.0384   0.0231   1.0000
  15.750   1.2610   0.08996   0.08266  -0.0394   0.0221   1.0000
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