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GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 682 AIRFOIL (goe682-il)
Reynolds number: 200,000
Max Cl/Cd: 78.66 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe682-il-200000.txt
Download as CSV file: xf-goe682-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 682 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3563   0.08919   0.08593  -0.0311   1.0000   0.0661
  -7.750  -0.3727   0.08820   0.08502  -0.0276   1.0000   0.0667
  -7.500  -0.3771   0.08618   0.08305  -0.0276   0.9980   0.0680
  -7.250  -0.3561   0.08003   0.07688  -0.0413   0.9883   0.0730
  -7.000  -0.3347   0.06947   0.06619  -0.0608   0.9773   0.0758
  -6.750  -0.3101   0.06799   0.06474  -0.0590   0.9740   0.0775
  -6.500  -0.2797   0.06497   0.06167  -0.0630   0.9705   0.0811
  -6.250  -0.2540   0.05479   0.05112  -0.0802   0.9584   0.0895
  -6.000  -0.2226   0.05266   0.04904  -0.0817   0.9561   0.0914
  -5.750  -0.2003   0.05047   0.04681  -0.0829   0.9473   0.0947
  -5.500  -0.1652   0.04476   0.04078  -0.0911   0.9426   0.1052
  -5.250  -0.1454   0.03144   0.02607  -0.0961   0.9317   0.0736
  -5.000  -0.1116   0.02705   0.02129  -0.0990   0.9283   0.0704
  -4.750  -0.0734   0.02417   0.01792  -0.1015   0.9257   0.0703
  -4.500  -0.0482   0.02225   0.01564  -0.1010   0.9157   0.0701
  -4.250  -0.0093   0.02039   0.01342  -0.1030   0.9115   0.0707
  -4.000   0.0195   0.01919   0.01196  -0.1028   0.9021   0.0717
  -3.750   0.0554   0.01828   0.01081  -0.1039   0.8964   0.0739
  -3.500   0.0832   0.01712   0.00950  -0.1037   0.8877   0.0760
  -3.250   0.1150   0.01605   0.00840  -0.1042   0.8811   0.0788
  -3.000   0.1423   0.01543   0.00776  -0.1038   0.8719   0.0819
  -2.750   0.1734   0.01483   0.00709  -0.1039   0.8647   0.0863
  -2.500   0.1985   0.01420   0.00647  -0.1032   0.8547   0.0921
  -2.250   0.2288   0.01369   0.00594  -0.1033   0.8477   0.0998
  -2.000   0.2529   0.01325   0.00556  -0.1023   0.8370   0.1099
  -1.750   0.2806   0.01287   0.00521  -0.1020   0.8287   0.1308
  -1.500   0.3063   0.01241   0.00503  -0.1014   0.8192   0.1928
  -1.250   0.3319   0.01214   0.00495  -0.1008   0.8099   0.2601
  -1.000   0.3592   0.01190   0.00480  -0.1005   0.8015   0.3080
  -0.750   0.3833   0.01165   0.00475  -0.0996   0.7912   0.3622
  -0.500   0.4060   0.01102   0.00469  -0.0985   0.7832   0.5209
  -0.250   0.4843   0.00989   0.00458  -0.1080   0.7746   1.0000
   0.000   0.5090   0.00995   0.00448  -0.1070   0.7641   1.0000
   0.250   0.5343   0.01000   0.00436  -0.1062   0.7535   1.0000
   0.500   0.5575   0.01008   0.00433  -0.1050   0.7409   1.0000
   0.750   0.5814   0.01015   0.00428  -0.1039   0.7287   1.0000
   1.000   0.6059   0.01023   0.00424  -0.1029   0.7167   1.0000
   1.250   0.6309   0.01031   0.00418  -0.1020   0.7048   1.0000
   1.500   0.6547   0.01040   0.00418  -0.1009   0.6918   1.0000
   1.750   0.6786   0.01051   0.00422  -0.0999   0.6792   1.0000
   2.000   0.7032   0.01064   0.00426  -0.0990   0.6675   1.0000
   2.250   0.7284   0.01078   0.00430  -0.0983   0.6564   1.0000
   2.500   0.7529   0.01091   0.00437  -0.0974   0.6443   1.0000
   2.750   0.7768   0.01105   0.00446  -0.0964   0.6313   1.0000
   3.000   0.8010   0.01120   0.00456  -0.0955   0.6183   1.0000
   3.250   0.8254   0.01136   0.00465  -0.0947   0.6056   1.0000
   3.500   0.8498   0.01153   0.00476  -0.0938   0.5931   1.0000
   3.750   0.8740   0.01170   0.00487  -0.0929   0.5802   1.0000
   4.000   0.8976   0.01186   0.00501  -0.0920   0.5661   1.0000
   4.250   0.9210   0.01203   0.00516  -0.0910   0.5516   1.0000
   4.500   0.9444   0.01222   0.00531  -0.0900   0.5368   1.0000
   4.750   0.9675   0.01241   0.00547  -0.0889   0.5217   1.0000
   5.000   0.9904   0.01263   0.00566  -0.0879   0.5065   1.0000
   5.250   1.0130   0.01288   0.00586  -0.0868   0.4907   1.0000
   5.500   1.0352   0.01316   0.00609  -0.0856   0.4742   1.0000
   5.750   1.0567   0.01348   0.00633  -0.0844   0.4569   1.0000
   6.000   1.0777   0.01383   0.00664  -0.0830   0.4384   1.0000
   6.250   1.0980   0.01420   0.00697  -0.0816   0.4186   1.0000
   6.500   1.1180   0.01463   0.00733  -0.0802   0.3991   1.0000
   6.750   1.1374   0.01509   0.00773  -0.0787   0.3802   1.0000
   7.000   1.1564   0.01558   0.00813  -0.0771   0.3621   1.0000
   7.250   1.1753   0.01602   0.00855  -0.0756   0.3442   1.0000
   7.500   1.1943   0.01651   0.00898  -0.0741   0.3293   1.0000
   7.750   1.2136   0.01702   0.00946  -0.0726   0.3170   1.0000
   8.000   1.2326   0.01748   0.00993  -0.0712   0.3045   1.0000
   8.250   1.2507   0.01796   0.01042  -0.0696   0.2923   1.0000
   8.500   1.2682   0.01848   0.01092  -0.0680   0.2809   1.0000
   8.750   1.2848   0.01905   0.01145  -0.0663   0.2702   1.0000
   9.000   1.3011   0.01954   0.01198  -0.0644   0.2594   1.0000
   9.250   1.3158   0.02005   0.01254  -0.0624   0.2489   1.0000
   9.500   1.3278   0.02063   0.01310  -0.0599   0.2382   1.0000
   9.750   1.3392   0.02121   0.01369  -0.0574   0.2277   1.0000
  10.000   1.3523   0.02173   0.01434  -0.0553   0.2180   1.0000
  10.250   1.3634   0.02240   0.01503  -0.0529   0.2086   1.0000
  10.500   1.3737   0.02305   0.01574  -0.0506   0.1979   1.0000
  10.750   1.3839   0.02372   0.01650  -0.0483   0.1847   1.0000
  11.000   1.3914   0.02456   0.01737  -0.0459   0.1679   1.0000
  11.250   1.3965   0.02566   0.01844  -0.0434   0.1356   1.0000
  11.500   1.3851   0.02807   0.02047  -0.0398   0.0903   1.0000
  11.750   1.3718   0.03096   0.02316  -0.0364   0.0646   1.0000
  12.000   1.3646   0.03357   0.02572  -0.0339   0.0525   1.0000
  12.250   1.3582   0.03624   0.02839  -0.0319   0.0471   1.0000
  12.500   1.3569   0.03862   0.03088  -0.0305   0.0434   1.0000
  12.750   1.3514   0.04149   0.03380  -0.0292   0.0408   1.0000
  13.000   1.3449   0.04461   0.03700  -0.0282   0.0390   1.0000
  13.250   1.3430   0.04741   0.03993  -0.0275   0.0373   1.0000
  13.500   1.3398   0.05044   0.04307  -0.0270   0.0360   1.0000
  13.750   1.3358   0.05367   0.04639  -0.0268   0.0349   1.0000
  14.000   1.3301   0.05720   0.04999  -0.0266   0.0339   1.0000
  14.250   1.3238   0.06083   0.05366  -0.0265   0.0331   1.0000
  14.500   1.3224   0.06398   0.05688  -0.0263   0.0323   1.0000
  14.750   1.3235   0.06694   0.05996  -0.0262   0.0316   1.0000
  15.000   1.3245   0.06996   0.06310  -0.0263   0.0307   1.0000
  15.250   1.3259   0.07296   0.06619  -0.0264   0.0298   1.0000
  15.500   1.3263   0.07614   0.06943  -0.0268   0.0288   1.0000
  15.750   1.3293   0.07894   0.07228  -0.0268   0.0281   1.0000
  16.000   1.3360   0.08112   0.07444  -0.0262   0.0273   1.0000
  16.250   1.3449   0.08316   0.07654  -0.0252   0.0267   1.0000
  16.500   1.3464   0.08646   0.08002  -0.0257   0.0264   1.0000
  16.750   1.3466   0.08999   0.08373  -0.0263   0.0261   1.0000
  17.000   1.3456   0.09380   0.08772  -0.0272   0.0258   1.0000
  17.250   1.3430   0.09790   0.09201  -0.0283   0.0256   1.0000
  17.500   1.3381   0.10246   0.09677  -0.0298   0.0254   1.0000
  17.750   1.3311   0.10744   0.10195  -0.0318   0.0252   1.0000
  18.000   1.3223   0.11286   0.10758  -0.0343   0.0250   1.0000
  18.250   1.3119   0.11868   0.11360  -0.0372   0.0248   1.0000
  18.500   1.2994   0.12507   0.12019  -0.0406   0.0248   1.0000
  18.750   1.2853   0.13196   0.12729  -0.0446   0.0248   1.0000
  19.000   1.2689   0.13958   0.13512  -0.0494   0.0247   1.0000
  19.250   1.2480   0.14856   0.14433  -0.0551   0.0250   1.0000
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