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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 200,000
Max Cl/Cd: 74.96 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe517-il-200000.txt
Download as CSV file: xf-goe517-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3478   0.08684   0.08349  -0.0254   1.0000   0.0375
  -7.250  -0.3530   0.08466   0.08139  -0.0249   1.0000   0.0383
  -7.000  -0.3547   0.08220   0.07899  -0.0255   1.0000   0.0393
  -6.750  -0.3570   0.07986   0.07671  -0.0269   1.0000   0.0405
  -6.500  -0.3607   0.07818   0.07506  -0.0298   1.0000   0.0416
  -6.250  -0.3635   0.07640   0.07328  -0.0302   1.0000   0.0419
  -6.000  -0.3634   0.07434   0.07117  -0.0309   1.0000   0.0421
  -5.750  -0.3548   0.06845   0.06528  -0.0328   0.9978   0.0428
  -5.500  -0.3358   0.06449   0.06136  -0.0335   0.9944   0.0442
  -5.250  -0.3089   0.06109   0.05792  -0.0367   0.9894   0.0472
  -5.000  -0.2436   0.05687   0.05316  -0.0509   0.9835   0.0538
  -4.750  -0.2289   0.05058   0.04695  -0.0526   0.9774   0.0553
  -4.500  -0.2002   0.04740   0.04375  -0.0551   0.9729   0.0575
  -4.250  -0.1652   0.04401   0.04021  -0.0590   0.9682   0.0619
  -4.000  -0.1258   0.03922   0.03493  -0.0637   0.9611   0.0680
  -3.750  -0.0929   0.03624   0.03194  -0.0664   0.9576   0.0705
  -3.500  -0.0579   0.03345   0.02865  -0.0684   0.9503   0.0815
  -3.250  -0.0227   0.02543   0.01993  -0.0695   0.9457   0.0511
  -3.000   0.0155   0.02054   0.01428  -0.0711   0.9429   0.0470
  -2.750   0.0470   0.01869   0.01203  -0.0715   0.9360   0.0500
  -2.500   0.0846   0.01713   0.01000  -0.0727   0.9313   0.0535
  -2.250   0.1237   0.01547   0.00822  -0.0748   0.9278   0.0592
  -2.000   0.1536   0.01482   0.00739  -0.0747   0.9187   0.0674
  -1.750   0.1920   0.01403   0.00655  -0.0763   0.9130   0.0797
  -1.500   0.2207   0.01332   0.00585  -0.0760   0.9018   0.0962
  -1.250   0.2501   0.01282   0.00538  -0.0759   0.8901   0.1151
  -1.000   0.2789   0.01241   0.00495  -0.0756   0.8780   0.1327
  -0.750   0.3066   0.01206   0.00459  -0.0751   0.8648   0.1502
  -0.500   0.3330   0.01171   0.00423  -0.0743   0.8506   0.1666
  -0.250   0.3583   0.01134   0.00393  -0.0734   0.8361   0.1861
   0.000   0.3831   0.01102   0.00369  -0.0724   0.8217   0.2155
   0.250   0.3968   0.00950   0.00354  -0.0696   0.8072   0.6394
   0.500   0.4894   0.00885   0.00324  -0.0826   0.7929   1.0000
   0.750   0.5130   0.00891   0.00317  -0.0813   0.7752   1.0000
   1.000   0.5367   0.00899   0.00311  -0.0802   0.7574   1.0000
   1.250   0.5607   0.00907   0.00306  -0.0790   0.7398   1.0000
   1.500   0.5843   0.00916   0.00304  -0.0779   0.7208   1.0000
   1.750   0.6080   0.00926   0.00304  -0.0768   0.7020   1.0000
   2.000   0.6319   0.00937   0.00304  -0.0758   0.6839   1.0000
   2.250   0.6558   0.00951   0.00308  -0.0748   0.6664   1.0000
   2.500   0.6796   0.00965   0.00314  -0.0737   0.6478   1.0000
   2.750   0.7033   0.00982   0.00322  -0.0727   0.6299   1.0000
   3.000   0.7270   0.01002   0.00332  -0.0717   0.6127   1.0000
   3.250   0.7506   0.01024   0.00346  -0.0707   0.5957   1.0000
   3.500   0.7740   0.01047   0.00362  -0.0697   0.5776   1.0000
   3.750   0.7973   0.01073   0.00381  -0.0687   0.5593   1.0000
   4.000   0.8205   0.01101   0.00403  -0.0677   0.5412   1.0000
   4.250   0.8435   0.01133   0.00428  -0.0666   0.5226   1.0000
   4.500   0.8662   0.01160   0.00454  -0.0655   0.5015   1.0000
   4.750   0.8888   0.01191   0.00480  -0.0644   0.4809   1.0000
   5.000   0.9113   0.01219   0.00507  -0.0634   0.4595   1.0000
   5.250   0.9335   0.01247   0.00531  -0.0622   0.4377   1.0000
   5.500   0.9558   0.01275   0.00559  -0.0611   0.4164   1.0000
   5.750   0.9781   0.01307   0.00589  -0.0601   0.3978   1.0000
   6.000   0.9998   0.01345   0.00620  -0.0589   0.3793   1.0000
   6.250   1.0208   0.01381   0.00653  -0.0577   0.3564   1.0000
   6.500   1.0410   0.01426   0.00691  -0.0564   0.3341   1.0000
   6.750   1.0619   0.01466   0.00732  -0.0553   0.3130   1.0000
   7.000   1.0826   0.01509   0.00775  -0.0541   0.2942   1.0000
   7.250   1.1033   0.01546   0.00817  -0.0529   0.2702   1.0000
   7.500   1.1222   0.01593   0.00863  -0.0514   0.2358   1.0000
   7.750   1.1264   0.01781   0.00966  -0.0482   0.0995   1.0000
   8.000   1.1306   0.01997   0.01149  -0.0447   0.0573   1.0000
   8.250   1.1409   0.02135   0.01293  -0.0420   0.0483   1.0000
   8.500   1.1509   0.02264   0.01426  -0.0394   0.0427   1.0000
   8.750   1.1597   0.02402   0.01572  -0.0366   0.0390   1.0000
   9.000   1.1709   0.02517   0.01696  -0.0342   0.0362   1.0000
   9.250   1.1789   0.02650   0.01835  -0.0314   0.0339   1.0000
   9.500   1.1854   0.02828   0.02014  -0.0285   0.0324   1.0000
   9.750   1.1983   0.03057   0.02250  -0.0266   0.0308   1.0000
  10.000   1.2120   0.03183   0.02392  -0.0247   0.0293   1.0000
  10.250   1.2265   0.03344   0.02568  -0.0231   0.0278   1.0000
  10.500   1.2426   0.03543   0.02781  -0.0217   0.0267   1.0000
  10.750   1.2582   0.03768   0.03024  -0.0204   0.0259   1.0000
  11.000   1.2727   0.04022   0.03302  -0.0191   0.0255   1.0000
  11.250   1.2836   0.04311   0.03617  -0.0174   0.0253   1.0000
  11.500   1.2887   0.04583   0.03913  -0.0153   0.0249   1.0000
  11.750   1.2900   0.04865   0.04218  -0.0131   0.0246   1.0000
  12.000   1.2889   0.05205   0.04575  -0.0112   0.0239   1.0000
  12.250   1.2804   0.05622   0.05017  -0.0091   0.0236   1.0000
  12.500   1.2719   0.05875   0.05295  -0.0070   0.0238   1.0000
  12.750   1.2584   0.06265   0.05709  -0.0055   0.0237   1.0000
  13.000   1.2446   0.06619   0.06086  -0.0046   0.0238   1.0000
  13.250   1.2289   0.07005   0.06498  -0.0044   0.0241   1.0000
  13.500   1.2011   0.07564   0.07094  -0.0055   0.0250   1.0000
  13.750   1.1690   0.08270   0.07832  -0.0084   0.0255   1.0000
  14.000   1.1350   0.09131   0.08722  -0.0131   0.0264   1.0000
  14.250   1.1075   0.09971   0.09582  -0.0183   0.0268   1.0000
  14.500   1.0746   0.11044   0.10673  -0.0252   0.0282   1.0000
  14.750   1.0469   0.12120   0.11761  -0.0321   0.0292   1.0000
  15.000   1.0230   0.13202   0.12847  -0.0388   0.0301   1.0000
  15.250   1.0064   0.14310   0.13964  -0.0451   0.0328   1.0000
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