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GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 572 AIRFOIL (goe572-il)
Reynolds number: 500,000
Max Cl/Cd: 77.53 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe572-il-500000-n5.txt
Download as CSV file: xf-goe572-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 572 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2181   0.02792   0.02290  -0.1420   0.5546   0.0136
 -10.250  -0.2327   0.02493   0.01951  -0.1366   0.5507   0.0139
 -10.000  -0.2262   0.02379   0.01819  -0.1334   0.5453   0.0142
  -9.750  -0.2097   0.02348   0.01782  -0.1315   0.5399   0.0146
  -9.500  -0.1959   0.02285   0.01708  -0.1292   0.5344   0.0149
  -9.250  -0.1790   0.02244   0.01659  -0.1273   0.5294   0.0153
  -9.000  -0.1668   0.02165   0.01562  -0.1246   0.5241   0.0157
  -8.750  -0.1523   0.02095   0.01475  -0.1223   0.5198   0.0163
  -8.500  -0.1397   0.01997   0.01355  -0.1196   0.5155   0.0169
  -8.250  -0.1254   0.01916   0.01253  -0.1171   0.5109   0.0174
  -8.000  -0.1069   0.01891   0.01220  -0.1153   0.5063   0.0178
  -7.750  -0.0858   0.01878   0.01204  -0.1140   0.5021   0.0183
  -7.500  -0.0665   0.01844   0.01161  -0.1123   0.4978   0.0188
  -7.250  -0.0466   0.01820   0.01127  -0.1106   0.4932   0.0197
  -7.000  -0.0289   0.01770   0.01059  -0.1086   0.4891   0.0204
  -6.750  -0.0092   0.01727   0.01001  -0.1070   0.4856   0.0213
  -6.500   0.0116   0.01710   0.00981  -0.1055   0.4814   0.0218
  -6.250   0.0322   0.01693   0.00959  -0.1040   0.4772   0.0224
  -6.000   0.0520   0.01677   0.00934  -0.1023   0.4728   0.0232
  -5.750   0.0730   0.01650   0.00896  -0.1008   0.4696   0.0241
  -5.500   0.0940   0.01620   0.00854  -0.0994   0.4660   0.0250
  -5.250   0.1142   0.01589   0.00813  -0.0978   0.4620   0.0258
  -5.000   0.1341   0.01569   0.00788  -0.0961   0.4581   0.0265
  -4.750   0.1544   0.01551   0.00765  -0.0945   0.4543   0.0272
  -4.500   0.1758   0.01531   0.00740  -0.0931   0.4508   0.0280
  -4.250   0.1965   0.01515   0.00717  -0.0916   0.4469   0.0290
  -4.000   0.2161   0.01501   0.00694  -0.0898   0.4432   0.0300
  -3.750   0.2349   0.01488   0.00670  -0.0879   0.4398   0.0306
  -3.500   0.2540   0.01452   0.00632  -0.0861   0.4367   0.0316
  -3.250   0.2738   0.01436   0.00614  -0.0844   0.4325   0.0325
  -3.000   0.2932   0.01420   0.00594  -0.0826   0.4289   0.0333
  -2.750   0.3117   0.01409   0.00576  -0.0806   0.4249   0.0341
  -2.500   0.3317   0.01398   0.00561  -0.0790   0.4217   0.0351
  -2.250   0.3524   0.01385   0.00544  -0.0775   0.4186   0.0359
  -2.000   0.3725   0.01375   0.00529  -0.0759   0.4149   0.0367
  -1.750   0.3910   0.01363   0.00513  -0.0739   0.4110   0.0374
  -1.500   0.4091   0.01355   0.00500  -0.0720   0.4077   0.0385
  -1.250   0.4300   0.01348   0.00492  -0.0705   0.4044   0.0396
  -1.000   0.4505   0.01346   0.00488  -0.0691   0.4002   0.0411
  -0.750   0.4705   0.01346   0.00484  -0.0675   0.3967   0.0427
  -0.500   0.4890   0.01349   0.00482  -0.0657   0.3929   0.0437
  -0.250   0.5095   0.01351   0.00481  -0.0642   0.3898   0.0447
   0.000   0.5301   0.01347   0.00478  -0.0628   0.3861   0.0481
   0.250   0.5502   0.01351   0.00479  -0.0614   0.3822   0.0509
   0.500   0.5694   0.01359   0.00483  -0.0598   0.3787   0.0538
   0.750   0.5885   0.01364   0.00489  -0.0581   0.3755   0.0613
   1.000   0.6097   0.01367   0.00493  -0.0570   0.3721   0.0702
   1.250   0.6297   0.01373   0.00501  -0.0556   0.3680   0.0845
   1.500   0.6491   0.01379   0.00510  -0.0541   0.3644   0.1066
   1.750   0.6673   0.01384   0.00525  -0.0526   0.3606   0.1537
   2.000   0.6892   0.01378   0.00539  -0.0518   0.3570   0.2322
   2.250   0.7141   0.01342   0.00562  -0.0519   0.3539   0.4549
   2.500   1.0459   0.01354   0.00672  -0.1187   0.3418   1.0000
   2.750   1.0620   0.01371   0.00685  -0.1166   0.3390   1.0000
   3.000   1.0777   0.01390   0.00700  -0.1144   0.3361   1.0000
   3.250   1.0929   0.01412   0.00718  -0.1122   0.3334   1.0000
   3.500   1.1072   0.01437   0.00739  -0.1099   0.3306   1.0000
   3.750   1.1247   0.01456   0.00757  -0.1082   0.3283   1.0000
   4.000   1.1417   0.01477   0.00777  -0.1065   0.3258   1.0000
   4.250   1.1577   0.01502   0.00800  -0.1046   0.3226   1.0000
   4.500   1.1731   0.01530   0.00826  -0.1026   0.3199   1.0000
   4.750   1.1873   0.01563   0.00856  -0.1005   0.3172   1.0000
   5.000   1.2028   0.01594   0.00886  -0.0986   0.3148   1.0000
   5.250   1.2198   0.01622   0.00914  -0.0971   0.3126   1.0000
   5.500   1.2361   0.01654   0.00946  -0.0955   0.3103   1.0000
   5.750   1.2514   0.01690   0.00982  -0.0938   0.3077   1.0000
   6.000   1.2658   0.01731   0.01023  -0.0920   0.3053   1.0000
   6.250   1.2792   0.01778   0.01069  -0.0901   0.3031   1.0000
   6.500   1.2921   0.01830   0.01120  -0.0882   0.3009   1.0000
   6.750   1.3083   0.01871   0.01164  -0.0869   0.2991   1.0000
   7.000   1.3237   0.01917   0.01212  -0.0855   0.2971   1.0000
   7.250   1.3382   0.01969   0.01266  -0.0840   0.2949   1.0000
   7.500   1.3518   0.02028   0.01327  -0.0825   0.2928   1.0000
   8.000   1.3756   0.02170   0.01472  -0.0794   0.2886   1.0000
   8.250   1.3855   0.02257   0.01560  -0.0777   0.2861   1.0000
   8.500   1.3996   0.02325   0.01632  -0.0765   0.2844   1.0000
   8.750   1.4127   0.02401   0.01713  -0.0754   0.2819   1.0000
   9.000   1.4240   0.02491   0.01806  -0.0742   0.2789   1.0000
   9.250   1.4301   0.02618   0.01933  -0.0725   0.2742   1.0000
   9.500   1.4357   0.02755   0.02070  -0.0710   0.2711   1.0000
   9.750   1.4474   0.02855   0.02175  -0.0700   0.2681   1.0000
  10.000   1.4541   0.02996   0.02319  -0.0688   0.2627   1.0000
  10.250   1.4599   0.03147   0.02472  -0.0676   0.2600   1.0000
  10.500   1.4624   0.03330   0.02658  -0.0663   0.2568   1.0000
  10.750   1.4689   0.03486   0.02818  -0.0654   0.2526   1.0000
  11.000   1.4747   0.03650   0.02987  -0.0645   0.2494   1.0000
  11.250   1.4738   0.03878   0.03219  -0.0633   0.2447   1.0000
  11.500   1.4704   0.04138   0.03480  -0.0622   0.2402   1.0000
  11.750   1.4736   0.04340   0.03688  -0.0614   0.2362   1.0000
  12.000   1.4660   0.04649   0.03999  -0.0603   0.2296   1.0000
  12.250   1.4591   0.04961   0.04313  -0.0593   0.2247   1.0000
  12.500   1.4493   0.05309   0.04664  -0.0584   0.2165   1.0000
  12.750   1.4375   0.05685   0.05042  -0.0575   0.2106   1.0000
  13.000   1.4305   0.06017   0.05379  -0.0568   0.2049   1.0000
  13.250   1.4149   0.06452   0.05815  -0.0560   0.1979   1.0000
  13.500   1.3896   0.07004   0.06368  -0.0552   0.1858   1.0000
  13.750   1.3647   0.07569   0.06933  -0.0546   0.1723   1.0000
  14.000   1.3475   0.08056   0.07421  -0.0542   0.1618   1.0000
  14.250   1.3138   0.08754   0.08118  -0.0538   0.1395   1.0000
  14.500   1.2890   0.09359   0.08726  -0.0537   0.1248   1.0000
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