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GOE 16K AIRFOIL (goe16k-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 16K AIRFOIL (goe16k-il)
Reynolds number: 500,000
Max Cl/Cd: 69.19 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe16k-il-500000.txt
Download as CSV file: xf-goe16k-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 16K AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -0.5631   0.09688   0.09369  -0.1463   0.9464   0.0336
 -18.000  -0.6319   0.08216   0.07866  -0.1553   0.9456   0.0334
 -17.750  -0.6630   0.07363   0.06992  -0.1613   0.9449   0.0335
 -17.250  -0.6991   0.06065   0.05653  -0.1714   0.9436   0.0343
 -17.000  -0.7252   0.05705   0.05284  -0.1693   0.9366   0.0344
 -16.750  -0.7118   0.05537   0.05120  -0.1713   0.9352   0.0351
 -16.500  -0.7231   0.05075   0.04638  -0.1738   0.9338   0.0350
 -16.250  -0.7120   0.04884   0.04444  -0.1758   0.9329   0.0357
 -16.000  -0.7055   0.04652   0.04204  -0.1777   0.9321   0.0365
 -15.750  -0.7008   0.04425   0.03965  -0.1792   0.9314   0.0371
 -15.500  -0.7224   0.04267   0.03796  -0.1743   0.9238   0.0375
 -15.250  -0.7231   0.04057   0.03571  -0.1736   0.9220   0.0379
 -15.000  -0.7251   0.03874   0.03365  -0.1726   0.9206   0.0388
 -14.750  -0.7222   0.03675   0.03148  -0.1718   0.9197   0.0393
 -14.500  -0.7101   0.03516   0.02984  -0.1716   0.9190   0.0398
 -14.250  -0.6940   0.03420   0.02888  -0.1716   0.9185   0.0406
 -14.000  -0.7106   0.03399   0.02865  -0.1645   0.9104   0.0410
 -13.750  -0.7021   0.03287   0.02743  -0.1629   0.9088   0.0414
 -13.500  -0.6914   0.03220   0.02668  -0.1613   0.9076   0.0424
 -13.250  -0.6801   0.03124   0.02559  -0.1598   0.9067   0.0432
 -13.000  -0.6710   0.03044   0.02462  -0.1578   0.9059   0.0444
 -12.750  -0.6561   0.02956   0.02361  -0.1567   0.9053   0.0447
 -12.500  -0.6748   0.02957   0.02352  -0.1483   0.8979   0.0449
 -12.250  -0.6606   0.02837   0.02233  -0.1470   0.8959   0.0463
 -12.000  -0.6451   0.02768   0.02161  -0.1455   0.8946   0.0470
 -11.750  -0.6292   0.02711   0.02099  -0.1442   0.8935   0.0479
 -11.500  -0.6124   0.02655   0.02035  -0.1428   0.8926   0.0490
 -11.250  -0.5937   0.02593   0.01963  -0.1418   0.8918   0.0501
 -11.000  -0.5739   0.02539   0.01897  -0.1410   0.8912   0.0509
 -10.750  -0.6057   0.02613   0.01964  -0.1291   0.8829   0.0513
 -10.500  -0.5920   0.02534   0.01875  -0.1269   0.8807   0.0521
 -10.250  -0.5662   0.02431   0.01773  -0.1275   0.8798   0.0532
 -10.000  -0.5474   0.02393   0.01734  -0.1262   0.8787   0.0543
  -9.750  -0.5264   0.02347   0.01684  -0.1254   0.8779   0.0553
  -9.500  -0.5025   0.02287   0.01617  -0.1252   0.8772   0.0565
  -9.250  -0.4789   0.02242   0.01564  -0.1249   0.8765   0.0578
  -9.000  -0.5478   0.02421   0.01742  -0.1051   0.8646   0.0571
  -8.750  -0.5312   0.02393   0.01709  -0.1032   0.8633   0.0579
  -8.500  -0.5114   0.02365   0.01672  -0.1018   0.8624   0.0589
  -8.250  -0.4852   0.02311   0.01611  -0.1019   0.8618   0.0593
  -8.000  -0.5727   0.02561   0.01860  -0.0788   0.8489   0.0589
  -7.750  -0.5504   0.02504   0.01798  -0.0781   0.8479   0.0600
  -7.500  -0.5247   0.02430   0.01724  -0.0782   0.8471   0.0613
  -7.250  -0.5027   0.02396   0.01690  -0.0774   0.8463   0.0628
  -7.000  -0.4809   0.02366   0.01658  -0.0764   0.8456   0.0638
  -6.750  -0.5241   0.02518   0.01807  -0.0625   0.8386   0.0639
  -6.500  -0.4777   0.02435   0.01720  -0.0664   0.8404   0.0656
  -6.250  -0.4387   0.02373   0.01653  -0.0689   0.8413   0.0670
  -6.000  -0.4021   0.02317   0.01592  -0.0710   0.8419   0.0681
  -5.750  -0.3685   0.02233   0.01508  -0.0724   0.8423   0.0702
  -2.750  -0.2798   0.02489   0.01755  -0.0266   0.8009   0.0985
  -2.500  -0.2479   0.02440   0.01742  -0.0280   0.7997   0.1632
  -2.250  -0.2172   0.02405   0.01735  -0.0290   0.7988   0.2233
  -2.000  -0.1876   0.02386   0.01729  -0.0296   0.7979   0.2576
  -1.750  -0.1572   0.02366   0.01722  -0.0304   0.7972   0.2895
  -1.500  -0.1265   0.02348   0.01715  -0.0313   0.7966   0.3211
  -1.250  -0.0954   0.02329   0.01708  -0.0322   0.7961   0.3506
  -1.000  -0.0638   0.02310   0.01698  -0.0332   0.7957   0.3789
  -0.750  -0.0328   0.02287   0.01687  -0.0340   0.7952   0.4135
  -0.500  -0.0027   0.02259   0.01678  -0.0348   0.7947   0.4579
  -0.250   0.1654   0.02398   0.02003  -0.0664   0.7968   0.8960
   0.000   0.1898   0.02402   0.02004  -0.0654   0.7961   0.9141
   0.250   0.2401   0.02449   0.02048  -0.0696   0.7958   0.9332
   0.750   0.2730   0.02662   0.02259  -0.0661   0.7840   0.9489
   1.000   0.3325   0.02715   0.02311  -0.0728   0.7839   0.9555
   1.250   0.3773   0.02724   0.02318  -0.0766   0.7833   0.9596
   1.500   0.4175   0.02722   0.02314  -0.0792   0.7828   0.9642
   1.750   0.4694   0.02725   0.02318  -0.0847   0.7826   0.9670
   2.000   0.5147   0.02716   0.02308  -0.0885   0.7823   0.9716
   2.250   0.5645   0.02681   0.02273  -0.0932   0.7821   0.9757
   2.500   0.6129   0.02657   0.02250  -0.0979   0.7819   0.9792
   2.750   0.6805   0.02620   0.02217  -0.1067   0.7824   0.9878
   3.000   0.8105   0.02295   0.01891  -0.1269   0.7959   0.9927
   3.250   0.8635   0.02177   0.01773  -0.1320   0.7962   0.9936
   3.500   0.9204   0.02053   0.01651  -0.1382   0.7963   0.9949
   3.750   0.9221   0.02080   0.01681  -0.1334   0.7880   0.9982
   4.000   1.1006   0.01653   0.01242  -0.1644   0.7940   0.9942
   4.250   1.0507   0.01735   0.01333  -0.1482   0.7834   0.9990
   4.500   1.1080   0.01623   0.01221  -0.1545   0.7803   0.9993
   4.750   1.1208   0.01620   0.01219  -0.1516   0.7751   0.9996
   8.000   1.0580   0.02514   0.01990  -0.0711   0.4408   1.0000
   8.250   1.0529   0.02638   0.02096  -0.0658   0.4104   1.0000
   8.500   1.0550   0.02734   0.02182  -0.0619   0.3888   1.0000
   8.750   1.0602   0.02818   0.02257  -0.0585   0.3638   1.0000
   9.000   1.0617   0.02925   0.02350  -0.0545   0.3327   1.0000
   9.250   1.0663   0.03019   0.02431  -0.0512   0.3038   1.0000
   9.500   1.0638   0.03153   0.02541  -0.0469   0.2584   1.0000
   9.750   1.0662   0.03265   0.02635  -0.0435   0.2262   1.0000
  10.000   1.0697   0.03373   0.02725  -0.0402   0.1972   1.0000
  10.250   1.0784   0.03454   0.02799  -0.0377   0.1807   1.0000
  10.500   1.0865   0.03542   0.02878  -0.0353   0.1637   1.0000
  10.750   1.0950   0.03629   0.02957  -0.0329   0.1479   1.0000
  11.000   1.1057   0.03706   0.03031  -0.0308   0.1383   1.0000
  11.250   1.1167   0.03781   0.03104  -0.0289   0.1283   1.0000
  11.500   1.1264   0.03866   0.03185  -0.0267   0.1170   1.0000
  11.750   1.1354   0.03959   0.03272  -0.0246   0.1078   1.0000
  12.000   1.1463   0.04040   0.03354  -0.0227   0.1010   1.0000
  12.250   1.1558   0.04131   0.03443  -0.0207   0.0949   1.0000
  12.500   1.1665   0.04215   0.03528  -0.0189   0.0886   1.0000
  12.750   1.1744   0.04320   0.03632  -0.0168   0.0834   1.0000
  13.000   1.1855   0.04406   0.03720  -0.0151   0.0778   1.0000
  13.250   1.1926   0.04519   0.03830  -0.0131   0.0732   1.0000
  13.500   1.2043   0.04604   0.03920  -0.0115   0.0691   1.0000
  13.750   1.2102   0.04731   0.04043  -0.0094   0.0641   1.0000
  14.000   1.2206   0.04828   0.04147  -0.0078   0.0610   1.0000
  14.250   1.2289   0.04941   0.04258  -0.0062   0.0569   1.0000
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