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GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 416A AIRFOIL (goe416a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.23 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe416a-il-1000000.txt
Download as CSV file: xf-goe416a-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 416A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5222   0.08503   0.08345  -0.0179   1.0000   0.0090
 -11.000  -0.5407   0.07723   0.07560  -0.0218   1.0000   0.0090
 -10.750  -0.6487   0.08844   0.08688  -0.0081   1.0000   0.0081
 -10.500  -0.6702   0.07802   0.07640  -0.0164   1.0000   0.0078
 -10.250  -0.6911   0.06984   0.06811  -0.0234   1.0000   0.0076
 -10.000  -0.7100   0.06306   0.06122  -0.0296   1.0000   0.0075
  -9.750  -0.7272   0.05753   0.05557  -0.0350   1.0000   0.0075
  -9.500  -0.7394   0.05340   0.05128  -0.0374   1.0000   0.0075
  -9.250  -0.7418   0.04946   0.04716  -0.0385   1.0000   0.0078
  -9.000  -0.7285   0.04706   0.04444  -0.0380   1.0000   0.0089
  -8.750  -0.7217   0.04413   0.04123  -0.0379   1.0000   0.0090
  -8.500  -0.7132   0.04091   0.03773  -0.0377   1.0000   0.0091
  -8.250  -0.7017   0.03784   0.03437  -0.0373   1.0000   0.0091
  -8.000  -0.6998   0.03011   0.02620  -0.0367   1.0000   0.0095
  -7.750  -0.6806   0.02805   0.02407  -0.0364   1.0000   0.0098
  -7.500  -0.6613   0.02640   0.02232  -0.0359   1.0000   0.0100
  -7.250  -0.6424   0.02492   0.02073  -0.0350   1.0000   0.0104
  -7.000  -0.6240   0.02356   0.01925  -0.0338   1.0000   0.0108
  -6.750  -0.5962   0.02214   0.01768  -0.0342   0.9985   0.0115
  -6.500  -0.5598   0.02320   0.01857  -0.0357   0.9961   0.0130
  -6.250  -0.5264   0.02196   0.01711  -0.0371   0.9940   0.0131
  -6.000  -0.4948   0.02021   0.01520  -0.0382   0.9901   0.0131
  -5.750  -0.4682   0.01377   0.00861  -0.0376   0.9862   0.0098
  -5.500  -0.4368   0.01290   0.00774  -0.0387   0.9807   0.0103
  -5.250  -0.4069   0.01220   0.00702  -0.0393   0.9730   0.0109
  -5.000  -0.3786   0.01152   0.00630  -0.0395   0.9634   0.0114
  -4.750  -0.3523   0.01090   0.00562  -0.0392   0.9518   0.0117
  -4.500  -0.3269   0.01038   0.00503  -0.0387   0.9394   0.0121
  -4.250  -0.3006   0.01011   0.00471  -0.0383   0.9275   0.0128
  -4.000  -0.2743   0.00970   0.00422  -0.0380   0.9155   0.0133
  -3.750  -0.2483   0.00893   0.00331  -0.0377   0.9025   0.0143
  -3.500  -0.2212   0.00861   0.00290  -0.0375   0.8890   0.0155
  -3.250  -0.1936   0.00837   0.00259  -0.0374   0.8754   0.0167
  -3.000  -0.1660   0.00820   0.00232  -0.0372   0.8590   0.0182
  -2.750  -0.1382   0.00804   0.00205  -0.0371   0.8408   0.0206
  -2.500  -0.1102   0.00790   0.00184  -0.0370   0.8218   0.0262
  -2.250  -0.0854   0.00589   0.00118  -0.0378   0.8010   0.4288
  -2.000  -0.0571   0.00593   0.00120  -0.0378   0.7784   0.4646
  -1.750  -0.0287   0.00603   0.00120  -0.0378   0.7536   0.4768
  -1.500  -0.0004   0.00611   0.00121  -0.0379   0.7268   0.4857
  -1.250   0.0282   0.00624   0.00121  -0.0379   0.7022   0.4931
  -0.750   0.0854   0.00646   0.00127  -0.0382   0.6614   0.5065
  -0.500   0.1140   0.00648   0.00124  -0.0383   0.6435   0.5098
  -0.250   0.1427   0.00654   0.00124  -0.0385   0.6269   0.5126
   0.000   0.1715   0.00660   0.00126  -0.0386   0.6126   0.5156
   0.250   0.2003   0.00667   0.00127  -0.0388   0.5989   0.5185
   0.500   0.2292   0.00674   0.00129  -0.0390   0.5836   0.5208
   0.750   0.2578   0.00678   0.00128  -0.0392   0.5667   0.5231
   1.000   0.2864   0.00683   0.00129  -0.0393   0.5479   0.5252
   1.250   0.3150   0.00690   0.00132  -0.0395   0.5238   0.5273
   1.500   0.3433   0.00703   0.00135  -0.0396   0.4957   0.5295
   1.750   0.3717   0.00716   0.00140  -0.0398   0.4712   0.5318
   2.000   0.4001   0.00729   0.00146  -0.0399   0.4525   0.5339
   2.250   0.4286   0.00741   0.00153  -0.0401   0.4382   0.5357
   2.500   0.4570   0.00747   0.00159  -0.0403   0.4256   0.5384
   2.750   0.4854   0.00755   0.00167  -0.0404   0.4134   0.5410
   3.000   0.5139   0.00765   0.00177  -0.0406   0.4026   0.5437
   3.250   0.5423   0.00776   0.00186  -0.0407   0.3906   0.5464
   3.500   0.5705   0.00790   0.00195  -0.0409   0.3676   0.5490
   3.750   0.5981   0.00811   0.00205  -0.0409   0.3301   0.5517
   4.000   0.6250   0.00844   0.00221  -0.0410   0.2799   0.5548
   4.250   0.6520   0.00877   0.00242  -0.0410   0.2477   0.5581
   4.500   0.6797   0.00898   0.00261  -0.0411   0.2325   0.5617
   4.750   0.7073   0.00920   0.00280  -0.0411   0.2192   0.5652
   5.000   0.7348   0.00939   0.00300  -0.0412   0.2052   0.5693
   5.250   0.7623   0.00959   0.00319  -0.0412   0.1902   0.5737
   5.500   0.7895   0.00984   0.00337  -0.0413   0.1669   0.5782
   5.750   0.8149   0.01037   0.00370  -0.0411   0.1185   0.5833
   6.000   0.8408   0.01080   0.00406  -0.0410   0.0942   0.5893
   6.250   0.8664   0.01128   0.00443  -0.0409   0.0671   0.5957
   6.500   0.8920   0.01173   0.00482  -0.0407   0.0492   0.6038
   6.750   0.9181   0.01208   0.00519  -0.0406   0.0403   0.6136
   7.000   0.9441   0.01242   0.00556  -0.0404   0.0317   0.6264
   7.250   0.9690   0.01292   0.00606  -0.0401   0.0202   0.6442
   7.500   0.9938   0.01338   0.00659  -0.0398   0.0152   0.6720
   7.750   1.0188   0.01365   0.00712  -0.0395   0.0134   0.7373
   8.000   1.0391   0.01355   0.00761  -0.0380   0.0121   1.0000
   8.250   1.0620   0.01439   0.00851  -0.0373   0.0104   1.0000
   8.500   1.0863   0.01494   0.00913  -0.0369   0.0099   1.0000
   8.750   1.1105   0.01547   0.00971  -0.0365   0.0093   1.0000
   9.000   1.1342   0.01603   0.01032  -0.0360   0.0086   1.0000
   9.250   1.1573   0.01665   0.01098  -0.0355   0.0080   1.0000
   9.500   1.1767   0.01770   0.01212  -0.0345   0.0074   1.0000
   9.750   1.1930   0.01908   0.01366  -0.0331   0.0070   1.0000
  10.000   1.2145   0.01976   0.01441  -0.0324   0.0068   1.0000
  10.250   1.2343   0.02057   0.01531  -0.0315   0.0065   1.0000
  10.500   1.2529   0.02149   0.01632  -0.0304   0.0063   1.0000
  10.750   1.2702   0.02248   0.01740  -0.0293   0.0060   1.0000
  11.000   1.2864   0.02349   0.01851  -0.0280   0.0058   1.0000
  11.250   1.3014   0.02455   0.01966  -0.0266   0.0056   1.0000
  11.500   1.3146   0.02566   0.02086  -0.0251   0.0054   1.0000
  11.750   1.3242   0.02681   0.02210  -0.0231   0.0053   1.0000
  12.000   1.3292   0.02816   0.02355  -0.0207   0.0052   1.0000
  12.250   1.3302   0.02994   0.02545  -0.0183   0.0050   1.0000
  12.500   1.3265   0.03233   0.02798  -0.0162   0.0049   1.0000
  12.750   1.3146   0.03580   0.03166  -0.0144   0.0048   1.0000
  13.250   1.2935   0.04363   0.03988  -0.0137   0.0046   1.0000
  13.500   1.2965   0.04635   0.04273  -0.0145   0.0045   1.0000
  13.750   1.2948   0.04987   0.04638  -0.0158   0.0045   1.0000
  14.000   1.2899   0.05403   0.05068  -0.0174   0.0044   1.0000
  14.250   1.2819   0.05876   0.05555  -0.0195   0.0044   1.0000
  14.500   1.2728   0.06388   0.06081  -0.0219   0.0044   1.0000
  14.750   1.2600   0.06971   0.06679  -0.0247   0.0043   1.0000
  15.000   1.2448   0.07616   0.07338  -0.0279   0.0043   1.0000
  15.250   1.2271   0.08324   0.08060  -0.0315   0.0043   1.0000
  15.500   1.2078   0.09084   0.08834  -0.0354   0.0043   1.0000
  15.750   1.1878   0.09889   0.09653  -0.0396   0.0043   1.0000
  16.000   1.1657   0.10767   0.10544  -0.0441   0.0043   1.0000
  16.250   1.1440   0.11674   0.11464  -0.0489   0.0044   1.0000
  16.500   1.1184   0.12695   0.12499  -0.0543   0.0044   1.0000
  16.750   1.0945   0.13715   0.13530  -0.0597   0.0045   1.0000
  17.000   1.0640   0.14949   0.14778  -0.0664   0.0045   1.0000
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