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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.93 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe177-il-1000000.txt
Download as CSV file: xf-goe177-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3302   0.08752   0.08606  -0.0194   1.0000   0.0082
  -7.250  -0.3288   0.08460   0.08318  -0.0202   1.0000   0.0082
  -7.000  -0.3244   0.08135   0.07995  -0.0221   0.9995   0.0082
  -6.750  -0.3049   0.07364   0.07224  -0.0322   0.9949   0.0086
  -6.500  -0.2798   0.06972   0.06831  -0.0383   0.9896   0.0089
  -6.250  -0.2517   0.06580   0.06437  -0.0448   0.9834   0.0092
  -6.000  -0.2252   0.06171   0.06025  -0.0510   0.9732   0.0098
  -5.750  -0.1977   0.05713   0.05561  -0.0574   0.9605   0.0109
  -5.500  -0.1643   0.05232   0.05072  -0.0639   0.9448   0.0124
  -5.250  -0.1184   0.01802   0.01501  -0.0890   0.9342   0.0085
  -5.000  -0.0937   0.01464   0.01105  -0.0892   0.9134   0.0087
  -4.750  -0.0692   0.01321   0.00928  -0.0887   0.8771   0.0092
  -4.500  -0.0442   0.01204   0.00768  -0.0880   0.8317   0.0094
  -4.250  -0.0179   0.01101   0.00625  -0.0876   0.7932   0.0096
  -4.000   0.0092   0.01047   0.00544  -0.0873   0.7622   0.0104
  -3.750   0.0368   0.00997   0.00473  -0.0871   0.7366   0.0112
  -3.500   0.0646   0.00967   0.00424  -0.0869   0.7155   0.0121
  -3.250   0.0926   0.00944   0.00386  -0.0868   0.6956   0.0125
  -3.000   0.1206   0.00857   0.00273  -0.0868   0.6756   0.0144
  -2.750   0.1486   0.00842   0.00249  -0.0867   0.6539   0.0167
  -2.500   0.1765   0.00833   0.00226  -0.0866   0.6324   0.0186
  -2.250   0.2048   0.00799   0.00179  -0.0865   0.6132   0.0241
  -2.000   0.2330   0.00781   0.00155  -0.0865   0.5958   0.0361
  -1.750   0.2611   0.00780   0.00158  -0.0865   0.5790   0.0621
  -1.500   0.2892   0.00784   0.00156  -0.0864   0.5630   0.0711
  -1.250   0.3173   0.00794   0.00158  -0.0864   0.5486   0.0752
  -1.000   0.3452   0.00792   0.00148  -0.0864   0.5305   0.0804
  -0.750   0.3730   0.00798   0.00145  -0.0864   0.5073   0.0850
  -0.500   0.4009   0.00805   0.00140  -0.0863   0.4853   0.0881
  -0.250   0.4288   0.00811   0.00136  -0.0863   0.4656   0.0892
   0.000   0.4567   0.00812   0.00127  -0.0863   0.4451   0.0930
   0.250   0.4846   0.00814   0.00124  -0.0863   0.4280   0.0979
   0.500   0.5125   0.00820   0.00122  -0.0863   0.4105   0.1015
   0.750   0.5403   0.00827   0.00122  -0.0863   0.3931   0.1089
   1.000   0.5681   0.00830   0.00124  -0.0863   0.3759   0.1302
   1.250   0.5959   0.00815   0.00133  -0.0865   0.3594   0.2556
   1.500   0.6236   0.00810   0.00144  -0.0866   0.3440   0.3565
   1.750   0.6422   0.00686   0.00161  -0.0849   0.3321   0.9380
   2.000   0.6723   0.00696   0.00163  -0.0853   0.3174   1.0000
   2.250   0.6999   0.00712   0.00170  -0.0853   0.3032   1.0000
   2.500   0.7273   0.00731   0.00179  -0.0853   0.2872   1.0000
   2.750   0.7545   0.00755   0.00190  -0.0852   0.2659   1.0000
   3.000   0.7809   0.00790   0.00205  -0.0851   0.2307   1.0000
   3.250   0.8023   0.00919   0.00270  -0.0844   0.1014   1.0000
   3.500   0.8278   0.00974   0.00303  -0.0841   0.0575   1.0000
   3.750   0.8548   0.00997   0.00324  -0.0840   0.0510   1.0000
   4.000   0.8820   0.01015   0.00341  -0.0839   0.0495   1.0000
   4.250   0.9092   0.01032   0.00358  -0.0839   0.0485   1.0000
   4.500   0.9363   0.01050   0.00378  -0.0838   0.0460   1.0000
   4.750   0.9629   0.01075   0.00399  -0.0837   0.0410   1.0000
   5.000   0.9899   0.01092   0.00414  -0.0836   0.0363   1.0000
   5.250   1.0154   0.01134   0.00446  -0.0833   0.0150   1.0000
   5.500   1.0414   0.01170   0.00487  -0.0831   0.0125   1.0000
   5.750   1.0673   0.01206   0.00532  -0.0827   0.0108   1.0000
   6.000   1.0928   0.01247   0.00578  -0.0824   0.0102   1.0000
   6.250   1.1181   0.01288   0.00623  -0.0820   0.0096   1.0000
   6.500   1.1427   0.01340   0.00680  -0.0815   0.0089   1.0000
   6.750   1.1668   0.01397   0.00744  -0.0810   0.0082   1.0000
   7.000   1.1902   0.01458   0.00811  -0.0804   0.0075   1.0000
   7.250   1.2123   0.01537   0.00897  -0.0796   0.0072   1.0000
   7.500   1.2318   0.01642   0.01011  -0.0784   0.0068   1.0000
   7.750   1.2442   0.01824   0.01204  -0.0763   0.0065   1.0000
   8.000   1.2635   0.01914   0.01301  -0.0751   0.0061   1.0000
   8.250   1.2846   0.01980   0.01374  -0.0742   0.0058   1.0000
   8.500   1.3016   0.02088   0.01490  -0.0727   0.0056   1.0000
   8.750   1.3157   0.02225   0.01634  -0.0707   0.0055   1.0000
   9.000   1.3277   0.02388   0.01804  -0.0685   0.0056   1.0000
   9.250   1.3394   0.02578   0.02000  -0.0663   0.0058   1.0000
   9.500   1.3543   0.02726   0.02155  -0.0646   0.0057   1.0000
   9.750   1.3695   0.02852   0.02291  -0.0630   0.0055   1.0000
  12.250   1.4098   0.05132   0.04726  -0.0416   0.0053   1.0000
  12.500   1.4023   0.05435   0.05046  -0.0409   0.0050   1.0000
  12.750   1.3936   0.05797   0.05424  -0.0408   0.0049   1.0000
  13.000   1.3843   0.06189   0.05831  -0.0412   0.0048   1.0000
  13.250   1.3737   0.06624   0.06281  -0.0421   0.0047   1.0000
  13.500   1.3622   0.07093   0.06764  -0.0433   0.0046   1.0000
  13.750   1.3488   0.07610   0.07297  -0.0451   0.0045   1.0000
  14.000   1.3346   0.08165   0.07866  -0.0472   0.0045   1.0000
  14.250   1.3191   0.08759   0.08475  -0.0498   0.0045   1.0000
  14.500   1.3033   0.09393   0.09123  -0.0527   0.0045   1.0000
  14.750   1.2870   0.10075   0.09819  -0.0562   0.0045   1.0000
  15.000   1.2696   0.10815   0.10574  -0.0602   0.0045   1.0000
  15.250   1.2532   0.11571   0.11344  -0.0644   0.0045   1.0000
  15.500   1.2356   0.12401   0.12188  -0.0693   0.0045   1.0000
  15.750   1.2193   0.13237   0.13036  -0.0743   0.0046   1.0000
  16.000   1.2007   0.14182   0.13995  -0.0801   0.0046   1.0000
  16.250   1.1837   0.15143   0.14968  -0.0861   0.0047   1.0000
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