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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.12 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe257-il-1000000.txt
Download as CSV file: xf-goe257-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4245   0.09981   0.09828  -0.0123   1.0000   0.0119
  -8.500  -0.4210   0.09597   0.09446  -0.0144   1.0000   0.0119
  -8.250  -0.4205   0.09158   0.09009  -0.0150   1.0000   0.0122
  -8.000  -0.4157   0.08880   0.08732  -0.0159   1.0000   0.0123
  -7.750  -0.4098   0.08594   0.08447  -0.0178   1.0000   0.0125
  -7.500  -0.3997   0.08276   0.08131  -0.0208   1.0000   0.0128
  -7.250  -0.3871   0.07917   0.07772  -0.0250   0.9973   0.0133
  -7.000  -0.3645   0.07427   0.07279  -0.0324   0.9805   0.0145
  -6.750  -0.3343   0.06624   0.06464  -0.0452   0.9585   0.0154
  -6.500  -0.3159   0.06119   0.05947  -0.0493   0.9370   0.0155
  -6.250  -0.2971   0.05623   0.05435  -0.0526   0.9136   0.0155
  -6.000  -0.2817   0.04880   0.04670  -0.0567   0.8885   0.0158
  -5.750  -0.2643   0.04726   0.04498  -0.0569   0.8446   0.0161
  -5.250  -0.2199   0.04347   0.04065  -0.0589   0.7491   0.0179
  -5.000  -0.1820   0.03853   0.03532  -0.0614   0.7340   0.0198
  -4.500  -0.1222   0.01416   0.01047  -0.0631   0.7000   0.0207
  -4.250  -0.0976   0.01318   0.00940  -0.0637   0.6930   0.0213
  -4.000  -0.0717   0.01194   0.00802  -0.0643   0.6870   0.0221
  -3.750  -0.0440   0.01070   0.00658  -0.0647   0.6810   0.0240
  -3.500  -0.0131   0.01021   0.00576  -0.0643   0.6755   0.0256
  -3.000   0.0427   0.01727   0.01189  -0.0679   0.6729   0.0268
  -2.750   0.0712   0.01632   0.01088  -0.0683   0.6671   0.0274
  -2.500   0.0999   0.01557   0.01001  -0.0687   0.6617   0.0282
  -2.250   0.1290   0.01485   0.00920  -0.0691   0.6562   0.0294
  -2.000   0.1582   0.01451   0.00874  -0.0693   0.6500   0.0316
  -1.750   0.1874   0.01515   0.00929  -0.0693   0.6435   0.0331
  -1.500   0.2169   0.01262   0.00652  -0.0698   0.6366   0.0355
  -1.250   0.2457   0.01207   0.00595  -0.0702   0.6296   0.0370
  -1.000   0.2747   0.01168   0.00552  -0.0704   0.6222   0.0392
  -0.750   0.3038   0.01145   0.00523  -0.0706   0.6157   0.0414
  -0.500   0.3325   0.01078   0.00452  -0.0710   0.6077   0.0476
  -0.250   0.3614   0.01046   0.00418  -0.0712   0.5994   0.0503
   0.000   0.3914   0.01009   0.00364  -0.0710   0.5911   0.0340
   0.250   0.4205   0.00957   0.00312  -0.0712   0.5832   0.0318
   0.500   0.4495   0.00933   0.00284  -0.0715   0.5737   0.0319
   0.750   0.4785   0.00918   0.00265  -0.0718   0.5616   0.0325
   1.000   0.5074   0.00910   0.00253  -0.0720   0.5472   0.0330
   1.250   0.5362   0.00906   0.00244  -0.0723   0.5323   0.0333
   1.500   0.5651   0.00898   0.00229  -0.0726   0.5162   0.0336
   1.750   0.5938   0.00897   0.00219  -0.0728   0.4955   0.0342
   2.250   0.6508   0.00911   0.00215  -0.0733   0.4574   0.0362
   2.750   0.7080   0.00925   0.00221  -0.0738   0.4331   0.0437
   3.000   0.7318   0.00724   0.00234  -0.0737   0.4235   1.0000
   3.250   0.7602   0.00739   0.00242  -0.0739   0.4136   1.0000
   3.500   0.7887   0.00751   0.00251  -0.0741   0.4052   1.0000
   3.750   0.8172   0.00764   0.00261  -0.0744   0.3968   1.0000
   4.000   0.8455   0.00781   0.00272  -0.0746   0.3831   1.0000
   4.250   0.8735   0.00801   0.00284  -0.0748   0.3612   1.0000
   4.500   0.9013   0.00826   0.00298  -0.0750   0.3333   1.0000
   4.750   0.9273   0.00892   0.00328  -0.0751   0.2635   1.0000
   5.000   0.9536   0.00946   0.00361  -0.0752   0.2239   1.0000
   5.250   0.9807   0.00983   0.00388  -0.0754   0.2038   1.0000
   5.500   1.0078   0.01016   0.00413  -0.0755   0.1859   1.0000
   5.750   1.0347   0.01050   0.00437  -0.0756   0.1648   1.0000
   6.000   1.0566   0.01180   0.00513  -0.0753   0.0672   1.0000
   6.250   1.0822   0.01233   0.00559  -0.0752   0.0462   1.0000
   6.500   1.1066   0.01306   0.00612  -0.0749   0.0182   1.0000
   6.750   1.1327   0.01347   0.00656  -0.0748   0.0152   1.0000
   7.000   1.1586   0.01386   0.00700  -0.0746   0.0142   1.0000
   7.250   1.1839   0.01431   0.00751  -0.0744   0.0130   1.0000
   7.500   1.2081   0.01493   0.00818  -0.0741   0.0118   1.0000
   7.750   1.2308   0.01575   0.00910  -0.0734   0.0109   1.0000
   8.000   1.2551   0.01624   0.00964  -0.0731   0.0106   1.0000
   8.250   1.2785   0.01682   0.01030  -0.0726   0.0101   1.0000
   8.500   1.3009   0.01748   0.01102  -0.0719   0.0097   1.0000
   8.750   1.3226   0.01818   0.01178  -0.0712   0.0092   1.0000
   9.000   1.3435   0.01890   0.01255  -0.0704   0.0088   1.0000
   9.250   1.3618   0.01984   0.01354  -0.0692   0.0083   1.0000
   9.500   1.3651   0.02214   0.01600  -0.0658   0.0077   1.0000
   9.750   1.3847   0.02274   0.01667  -0.0648   0.0076   1.0000
  10.000   1.4010   0.02356   0.01755  -0.0633   0.0074   1.0000
  10.250   1.4141   0.02456   0.01863  -0.0613   0.0072   1.0000
  10.500   1.4246   0.02566   0.01982  -0.0590   0.0070   1.0000
  10.750   1.4307   0.02687   0.02112  -0.0559   0.0069   1.0000
  11.000   1.4336   0.02822   0.02256  -0.0526   0.0068   1.0000
  11.250   1.4372   0.02974   0.02418  -0.0499   0.0066   1.0000
  11.500   1.4412   0.03140   0.02593  -0.0475   0.0065   1.0000
  11.750   1.4458   0.03314   0.02776  -0.0456   0.0063   1.0000
  12.000   1.4498   0.03505   0.02977  -0.0440   0.0062   1.0000
  12.250   1.4538   0.03708   0.03189  -0.0426   0.0061   1.0000
  12.500   1.4574   0.03924   0.03414  -0.0416   0.0060   1.0000
  12.750   1.4603   0.04160   0.03660  -0.0408   0.0058   1.0000
  13.000   1.4621   0.04419   0.03929  -0.0402   0.0057   1.0000
  13.250   1.4627   0.04698   0.04217  -0.0397   0.0056   1.0000
  13.500   1.4612   0.05006   0.04535  -0.0391   0.0055   1.0000
  13.750   1.4563   0.05359   0.04900  -0.0383   0.0054   1.0000
  14.000   1.4396   0.05878   0.05441  -0.0363   0.0053   1.0000
  14.250   1.4291   0.06328   0.05911  -0.0364   0.0052   1.0000
  14.500   1.4243   0.06703   0.06300  -0.0374   0.0051   1.0000
  14.750   1.4182   0.07111   0.06721  -0.0384   0.0051   1.0000
  15.000   1.4102   0.07566   0.07191  -0.0396   0.0050   1.0000
  15.250   1.4009   0.08056   0.07697  -0.0410   0.0050   1.0000
  15.500   1.3895   0.08598   0.08254  -0.0427   0.0050   1.0000
  15.750   1.3763   0.09194   0.08866  -0.0448   0.0049   1.0000
  16.000   1.3619   0.09833   0.09520  -0.0473   0.0049   1.0000
  16.250   1.3470   0.10503   0.10206  -0.0502   0.0049   1.0000
  16.500   1.3310   0.11221   0.10939  -0.0536   0.0049   1.0000
  16.750   1.3149   0.11969   0.11703  -0.0573   0.0049   1.0000
  17.000   1.2983   0.12755   0.12503  -0.0615   0.0050   1.0000
  17.250   1.2804   0.13595   0.13358  -0.0661   0.0050   1.0000
  17.500   1.2622   0.14491   0.14269  -0.0714   0.0050   1.0000
  17.750   1.2439   0.15440   0.15232  -0.0771   0.0050   1.0000
  18.000   1.2245   0.16471   0.16276  -0.0836   0.0051   1.0000
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