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GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 777 AIRFOIL (goe777-il)
Reynolds number: 200,000
Max Cl/Cd: 54.58 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe777-il-200000.txt
Download as CSV file: xf-goe777-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 777 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.5098   0.07043   0.06524  -0.0811   0.6800   0.0614
 -13.250  -0.5457   0.06318   0.05777  -0.0859   0.6766   0.0611
 -13.000  -0.5817   0.05720   0.05149  -0.0888   0.6730   0.0609
 -12.750  -0.6139   0.05249   0.04644  -0.0893   0.6692   0.0609
 -12.500  -0.6416   0.04867   0.04230  -0.0876   0.6648   0.0611
 -12.250  -0.6651   0.04560   0.03882  -0.0843   0.6604   0.0614
 -12.000  -0.6631   0.04323   0.03623  -0.0828   0.6553   0.0620
 -11.750  -0.6398   0.04245   0.03548  -0.0825   0.6501   0.0628
 -11.500  -0.6245   0.04131   0.03424  -0.0816   0.6459   0.0635
 -11.250  -0.6135   0.03972   0.03249  -0.0804   0.6419   0.0644
 -11.000  -0.6041   0.03797   0.03048  -0.0789   0.6381   0.0656
 -10.750  -0.5972   0.03603   0.02812  -0.0769   0.6347   0.0670
 -10.500  -0.5838   0.03435   0.02614  -0.0755   0.6315   0.0683
 -10.250  -0.5594   0.03357   0.02537  -0.0752   0.6282   0.0694
 -10.000  -0.5373   0.03275   0.02446  -0.0747   0.6252   0.0708
  -9.750  -0.5172   0.03163   0.02317  -0.0738   0.6225   0.0724
  -9.500  -0.4998   0.03057   0.02174  -0.0724   0.6197   0.0743
  -9.250  -0.4744   0.02954   0.02078  -0.0723   0.6166   0.0760
  -9.000  -0.4495   0.02892   0.02014  -0.0719   0.6135   0.0780
  -8.750  -0.4265   0.02816   0.01918  -0.0712   0.6107   0.0805
  -8.500  -0.4026   0.02722   0.01807  -0.0706   0.6082   0.0827
  -8.250  -0.3766   0.02664   0.01749  -0.0704   0.6060   0.0851
  -8.000  -0.3518   0.02620   0.01695  -0.0699   0.6038   0.0884
  -7.750  -0.3262   0.02542   0.01615  -0.0696   0.6018   0.0916
  -7.500  -0.3003   0.02491   0.01570  -0.0694   0.5997   0.0950
  -7.250  -0.2752   0.02457   0.01519  -0.0688   0.5975   0.0988
  -7.000  -0.2485   0.02379   0.01458  -0.0688   0.5951   0.1027
  -6.750  -0.2229   0.02345   0.01416  -0.0684   0.5926   0.1072
  -6.500  -0.1969   0.02284   0.01359  -0.0681   0.5902   0.1114
  -6.250  -0.1709   0.02251   0.01326  -0.0677   0.5883   0.1160
  -6.000  -0.1450   0.02216   0.01286  -0.0674   0.5864   0.1206
  -5.750  -0.1197   0.02185   0.01260  -0.0670   0.5846   0.1254
  -5.500  -0.0941   0.02178   0.01248  -0.0666   0.5824   0.1303
  -5.250  -0.0702   0.02131   0.01214  -0.0660   0.5797   0.1354
  -5.000  -0.0453   0.02105   0.01193  -0.0655   0.5762   0.1412
  -4.750  -0.0212   0.02068   0.01161  -0.0648   0.5726   0.1474
  -4.500   0.0037   0.02038   0.01130  -0.0642   0.5690   0.1550
  -4.250   0.0283   0.02003   0.01098  -0.0635   0.5660   0.1637
  -4.000   0.0531   0.01983   0.01078  -0.0630   0.5635   0.1761
  -3.750   0.0758   0.01962   0.01075  -0.0622   0.5612   0.2015
  -3.500   0.0939   0.01893   0.01067  -0.0609   0.5587   0.3048
  -3.250   0.1131   0.01847   0.01067  -0.0595   0.5558   0.4065
  -3.000   0.1334   0.01818   0.01079  -0.0581   0.5529   0.4889
  -2.750   0.1568   0.01816   0.01099  -0.0570   0.5501   0.5580
  -2.500   0.1823   0.01825   0.01111  -0.0563   0.5475   0.6006
  -2.250   0.2087   0.01832   0.01119  -0.0556   0.5450   0.6310
  -2.000   0.2359   0.01848   0.01131  -0.0552   0.5425   0.6562
  -1.750   0.2608   0.01874   0.01161  -0.0544   0.5396   0.6801
  -1.500   0.2845   0.01887   0.01185  -0.0534   0.5361   0.7040
  -1.250   0.3094   0.01898   0.01202  -0.0526   0.5326   0.7252
  -1.000   0.3353   0.01905   0.01212  -0.0520   0.5293   0.7439
  -0.750   0.3619   0.01910   0.01215  -0.0514   0.5263   0.7621
  -0.500   0.3893   0.01916   0.01216  -0.0509   0.5237   0.7797
  -0.250   0.4172   0.01937   0.01233  -0.0505   0.5210   0.7956
   0.000   0.4397   0.01956   0.01263  -0.0495   0.5173   0.8116
   0.250   0.4631   0.01969   0.01280  -0.0486   0.5130   0.8286
   0.500   0.4885   0.01971   0.01286  -0.0477   0.5091   0.8453
   0.750   0.5158   0.01967   0.01279  -0.0472   0.5057   0.8621
   1.000   0.5453   0.01963   0.01268  -0.0470   0.5028   0.8787
   1.250   0.5737   0.01984   0.01283  -0.0469   0.4995   0.8948
   1.500   0.5978   0.02001   0.01312  -0.0463   0.4945   0.9119
   1.750   0.6328   0.02012   0.01324  -0.0476   0.4898   0.9259
   2.000   0.6740   0.02012   0.01316  -0.0499   0.4861   0.9385
   2.250   0.7190   0.02013   0.01302  -0.0529   0.4829   0.9509
   2.500   0.7616   0.02041   0.01330  -0.0560   0.4781   0.9622
   2.750   0.8069   0.02056   0.01348  -0.0599   0.4719   0.9696
   3.000   0.8514   0.02046   0.01329  -0.0634   0.4676   0.9789
   3.250   0.9025   0.02026   0.01293  -0.0680   0.4640   0.9842
   3.500   0.9457   0.02047   0.01318  -0.0718   0.4581   0.9930
   3.750   0.9925   0.02048   0.01319  -0.0761   0.4522   0.9998
   4.000   1.0050   0.02034   0.01296  -0.0740   0.4489   1.0000
   4.250   1.0229   0.02022   0.01271  -0.0725   0.4460   1.0000
   4.500   1.0304   0.02050   0.01304  -0.0695   0.4413   1.0000
   4.750   1.0414   0.02071   0.01328  -0.0669   0.4364   1.0000
   5.000   1.0608   0.02074   0.01324  -0.0656   0.4326   1.0000
   5.250   1.0846   0.02070   0.01309  -0.0650   0.4296   1.0000
   5.500   1.1025   0.02096   0.01332  -0.0636   0.4259   1.0000
   5.750   1.1127   0.02139   0.01383  -0.0609   0.4211   1.0000
   6.000   1.1316   0.02157   0.01398  -0.0597   0.4173   1.0000
   6.250   1.1552   0.02162   0.01396  -0.0591   0.4142   1.0000
   6.500   1.1834   0.02168   0.01388  -0.0593   0.4114   1.0000
   6.750   1.1908   0.02232   0.01465  -0.0565   0.4071   1.0000
   7.000   1.2057   0.02277   0.01514  -0.0549   0.4034   1.0000
   7.250   1.2261   0.02306   0.01541  -0.0540   0.4004   1.0000
   7.500   1.2502   0.02326   0.01555  -0.0537   0.3978   1.0000
   7.750   1.2799   0.02346   0.01564  -0.0543   0.3954   1.0000
   8.000   1.2873   0.02427   0.01657  -0.0518   0.3924   1.0000
   8.250   1.2937   0.02505   0.01744  -0.0492   0.3893   1.0000
   8.500   1.3058   0.02568   0.01810  -0.0474   0.3866   1.0000
   8.750   1.3245   0.02615   0.01856  -0.0466   0.3842   1.0000
   9.000   1.3493   0.02645   0.01883  -0.0466   0.3819   1.0000
   9.250   1.3824   0.02665   0.01894  -0.0478   0.3798   1.0000
   9.500   1.3855   0.02775   0.02014  -0.0452   0.3773   1.0000
   9.750   1.3780   0.02935   0.02190  -0.0418   0.3746   1.0000
  10.000   1.3780   0.03086   0.02351  -0.0396   0.3720   1.0000
  10.250   1.3867   0.03205   0.02476  -0.0385   0.3697   1.0000
  10.500   1.4044   0.03282   0.02554  -0.0381   0.3677   1.0000
  10.750   1.4314   0.03315   0.02585  -0.0384   0.3660   1.0000
  11.000   1.4683   0.03309   0.02573  -0.0396   0.3644   1.0000
  11.250   1.4791   0.03440   0.02709  -0.0388   0.3623   1.0000
  11.500   0.8174   0.11431   0.10820  -0.0329   0.3154   1.0000
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