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GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 693 AIRFOIL (goe693-il)
Reynolds number: 200,000
Max Cl/Cd: 78.16 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe693-il-200000.txt
Download as CSV file: xf-goe693-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 693 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3912   0.08866   0.08519  -0.0399   1.0000   0.0846
  -8.250  -0.4121   0.08674   0.08336  -0.0376   1.0000   0.0859
  -8.000  -0.4430   0.08558   0.08233  -0.0336   1.0000   0.0865
  -7.750  -0.5050   0.05371   0.04979  -0.0655   0.9854   0.0672
  -7.500  -0.4796   0.04894   0.04487  -0.0691   0.9811   0.0646
  -7.250  -0.4659   0.04032   0.03565  -0.0736   0.9734   0.0636
  -7.000  -0.4426   0.03304   0.02756  -0.0773   0.9694   0.0633
  -6.750  -0.4193   0.02916   0.02306  -0.0782   0.9615   0.0643
  -6.500  -0.3842   0.02674   0.02004  -0.0805   0.9579   0.0662
  -6.250  -0.3473   0.02415   0.01719  -0.0833   0.9557   0.0681
  -6.000  -0.3179   0.02311   0.01605  -0.0839   0.9477   0.0700
  -5.750  -0.2791   0.02204   0.01482  -0.0863   0.9443   0.0729
  -5.500  -0.2397   0.02101   0.01349  -0.0887   0.9415   0.0765
  -5.250  -0.2107   0.01980   0.01219  -0.0891   0.9341   0.0795
  -5.000  -0.1759   0.01913   0.01150  -0.0905   0.9290   0.0835
  -4.750  -0.1387   0.01850   0.01068  -0.0921   0.9255   0.0892
  -4.500  -0.1128   0.01779   0.01003  -0.0919   0.9164   0.0951
  -4.250  -0.0793   0.01737   0.00945  -0.0927   0.9114   0.1031
  -4.000  -0.0519   0.01667   0.00884  -0.0926   0.9040   0.1120
  -3.750  -0.0226   0.01612   0.00826  -0.0928   0.8974   0.1228
  -3.500   0.0069   0.01579   0.00785  -0.0929   0.8913   0.1340
  -3.250   0.0336   0.01539   0.00751  -0.0927   0.8834   0.1447
  -3.000   0.0634   0.01494   0.00706  -0.0929   0.8785   0.1556
  -2.750   0.0891   0.01475   0.00684  -0.0924   0.8696   0.1662
  -2.500   0.1179   0.01441   0.00652  -0.0924   0.8641   0.1777
  -2.250   0.1440   0.01414   0.00630  -0.0920   0.8561   0.1888
  -2.000   0.1719   0.01381   0.00599  -0.0918   0.8494   0.2017
  -1.750   0.1983   0.01355   0.00578  -0.0914   0.8412   0.2176
  -1.500   0.2255   0.01318   0.00550  -0.0910   0.8337   0.2408
  -1.250   0.2509   0.01277   0.00533  -0.0905   0.8253   0.2880
  -1.000   0.2740   0.01187   0.00515  -0.0897   0.8179   0.4659
  -0.750   0.2886   0.01080   0.00531  -0.0860   0.8098   0.8049
  -0.500   0.3613   0.01063   0.00523  -0.0940   0.8030   0.9859
  -0.250   0.4062   0.01064   0.00510  -0.0976   0.7952   1.0000
   0.000   0.4311   0.01067   0.00500  -0.0969   0.7871   1.0000
   0.250   0.4558   0.01074   0.00497  -0.0962   0.7790   1.0000
   0.500   0.4811   0.01078   0.00490  -0.0955   0.7708   1.0000
   0.750   0.5058   0.01086   0.00490  -0.0948   0.7625   1.0000
   1.000   0.5313   0.01092   0.00487  -0.0942   0.7546   1.0000
   1.250   0.5562   0.01102   0.00491  -0.0935   0.7464   1.0000
   1.500   0.5819   0.01109   0.00489  -0.0929   0.7385   1.0000
   1.750   0.6068   0.01119   0.00496  -0.0922   0.7299   1.0000
   2.000   0.6328   0.01126   0.00494  -0.0916   0.7217   1.0000
   2.250   0.6576   0.01137   0.00504  -0.0909   0.7125   1.0000
   2.500   0.6842   0.01145   0.00503  -0.0905   0.7048   1.0000
   2.750   0.7090   0.01156   0.00516  -0.0898   0.6953   1.0000
   3.000   0.7356   0.01165   0.00519  -0.0894   0.6873   1.0000
   3.250   0.7605   0.01175   0.00529  -0.0887   0.6768   1.0000
   3.500   0.7861   0.01184   0.00537  -0.0881   0.6666   1.0000
   3.750   0.8124   0.01191   0.00538  -0.0876   0.6563   1.0000
   4.000   0.8370   0.01198   0.00547  -0.0868   0.6432   1.0000
   4.250   0.8618   0.01205   0.00554  -0.0861   0.6292   1.0000
   4.500   0.8866   0.01213   0.00560  -0.0853   0.6144   1.0000
   4.750   0.9111   0.01222   0.00568  -0.0845   0.5981   1.0000
   5.000   0.9354   0.01233   0.00575  -0.0836   0.5803   1.0000
   5.250   0.9593   0.01247   0.00585  -0.0827   0.5614   1.0000
   5.500   0.9826   0.01265   0.00602  -0.0818   0.5397   1.0000
   5.750   1.0055   0.01288   0.00617  -0.0808   0.5174   1.0000
   6.000   1.0278   0.01315   0.00639  -0.0797   0.4934   1.0000
   6.250   1.0492   0.01351   0.00663  -0.0784   0.4697   1.0000
   6.500   1.0707   0.01389   0.00695  -0.0773   0.4475   1.0000
   6.750   1.0920   0.01431   0.00730  -0.0761   0.4280   1.0000
   7.000   1.1127   0.01477   0.00768  -0.0749   0.4092   1.0000
   7.250   1.1330   0.01527   0.00811  -0.0736   0.3913   1.0000
   7.500   1.1532   0.01575   0.00856  -0.0724   0.3739   1.0000
   7.750   1.1726   0.01625   0.00905  -0.0710   0.3556   1.0000
   8.000   1.1908   0.01680   0.00957  -0.0694   0.3358   1.0000
   8.250   1.2066   0.01742   0.01011  -0.0675   0.3141   1.0000
   8.500   1.2222   0.01798   0.01065  -0.0656   0.2893   1.0000
   8.750   1.2360   0.01861   0.01120  -0.0634   0.2651   1.0000
   9.000   1.2499   0.01923   0.01178  -0.0613   0.2418   1.0000
   9.250   1.2603   0.01994   0.01242  -0.0586   0.2231   1.0000
   9.500   1.2703   0.02074   0.01315  -0.0559   0.2069   1.0000
   9.750   1.2794   0.02166   0.01400  -0.0533   0.1926   1.0000
  10.000   1.2884   0.02266   0.01495  -0.0508   0.1805   1.0000
  10.250   1.2992   0.02361   0.01593  -0.0487   0.1692   1.0000
  10.500   1.3094   0.02462   0.01699  -0.0466   0.1581   1.0000
  10.750   1.3189   0.02570   0.01808  -0.0446   0.1464   1.0000
  11.000   1.3311   0.02662   0.01908  -0.0430   0.1306   1.0000
  11.250   1.3402   0.02780   0.02018  -0.0412   0.1025   1.0000
  11.500   1.3360   0.03009   0.02223  -0.0384   0.0785   1.0000
  11.750   1.3308   0.03261   0.02466  -0.0357   0.0628   1.0000
  12.000   1.3317   0.03475   0.02679  -0.0338   0.0533   1.0000
  12.250   1.3342   0.03682   0.02892  -0.0321   0.0481   1.0000
  12.500   1.3322   0.03936   0.03146  -0.0305   0.0450   1.0000
  12.750   1.3329   0.04172   0.03392  -0.0292   0.0426   1.0000
  13.000   1.3338   0.04413   0.03643  -0.0280   0.0406   1.0000
  13.250   1.3323   0.04683   0.03917  -0.0269   0.0389   1.0000
  13.500   1.3262   0.05000   0.04235  -0.0257   0.0374   1.0000
  13.750   1.3284   0.05246   0.04495  -0.0249   0.0362   1.0000
  14.000   1.3297   0.05505   0.04766  -0.0241   0.0351   1.0000
  14.250   1.3308   0.05769   0.05038  -0.0234   0.0341   1.0000
  14.500   1.3321   0.06033   0.05308  -0.0227   0.0332   1.0000
  14.750   1.3340   0.06291   0.05570  -0.0219   0.0324   1.0000
  15.000   1.3377   0.06520   0.05798  -0.0207   0.0315   1.0000
  15.250   1.3427   0.06752   0.06038  -0.0196   0.0308   1.0000
  15.500   1.3451   0.07026   0.06330  -0.0193   0.0301   1.0000
  15.750   1.3470   0.07311   0.06630  -0.0190   0.0294   1.0000
  16.000   1.3487   0.07599   0.06932  -0.0188   0.0287   1.0000
  16.250   1.3497   0.07901   0.07247  -0.0187   0.0281   1.0000
  16.500   1.3505   0.08208   0.07566  -0.0187   0.0276   1.0000
  16.750   1.3517   0.08516   0.07885  -0.0187   0.0272   1.0000
  17.000   1.3524   0.08833   0.08212  -0.0188   0.0268   1.0000
  17.250   1.3529   0.09156   0.08545  -0.0188   0.0264   1.0000
  17.500   1.3529   0.09497   0.08898  -0.0187   0.0261   1.0000
  17.750   1.3482   0.09924   0.09342  -0.0192   0.0259   1.0000
  18.000   1.3384   0.10434   0.09872  -0.0206   0.0258   1.0000
  18.250   1.3253   0.11003   0.10461  -0.0228   0.0257   1.0000
  18.500   1.3103   0.11621   0.11102  -0.0258   0.0257   1.0000
  18.750   1.2947   0.12281   0.11783  -0.0293   0.0257   1.0000
  19.000   1.2781   0.12990   0.12514  -0.0334   0.0257   1.0000
  19.250   1.2603   0.13764   0.13310  -0.0385   0.0258   1.0000
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