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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 500,000
Max Cl/Cd: 110.48 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe528-il-500000.txt
Download as CSV file: xf-goe528-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0715   0.09088   0.08867  -0.0749   0.9504   0.0286
 -10.250  -0.1752   0.10434   0.10209  -0.0552   0.9846   0.0259
 -10.000  -0.1612   0.10079   0.09854  -0.0585   0.9738   0.0268
  -9.750  -0.1568   0.09412   0.09186  -0.0691   0.9600   0.0286
  -9.500  -0.1386   0.08931   0.08703  -0.0732   0.9513   0.0289
  -9.250  -0.1093   0.08610   0.08380  -0.0771   0.9445   0.0293
  -9.000  -0.0778   0.08239   0.08004  -0.0834   0.9369   0.0300
  -8.750  -0.0446   0.07799   0.07558  -0.0919   0.9270   0.0311
  -8.500  -0.0308   0.06849   0.06594  -0.1097   0.9008   0.0336
  -8.250  -0.0132   0.06629   0.06366  -0.1104   0.8859   0.0340
  -8.000  -0.0009   0.06452   0.06182  -0.1107   0.8708   0.0344
  -7.750   0.0031   0.06252   0.05976  -0.1108   0.8562   0.0347
  -7.500   0.0069   0.06051   0.05769  -0.1112   0.8434   0.0353
  -7.250   0.0114   0.05787   0.05499  -0.1127   0.8311   0.0361
  -7.000  -0.0057   0.04512   0.04196  -0.1264   0.8168   0.0393
  -6.750   0.0089   0.04419   0.04102  -0.1253   0.8082   0.0397
  -6.500   0.0246   0.04328   0.04008  -0.1245   0.7990   0.0402
  -6.250   0.0407   0.04188   0.03861  -0.1244   0.7905   0.0409
  -6.000   0.0434   0.03320   0.02921  -0.1281   0.7815   0.0460
  -5.750   0.0629   0.03161   0.02765  -0.1277   0.7733   0.0465
  -5.500   0.0832   0.03049   0.02648  -0.1273   0.7646   0.0472
  -5.250   0.1038   0.02920   0.02511  -0.1269   0.7561   0.0482
  -5.000   0.1199   0.02584   0.02110  -0.1263   0.7477   0.0540
  -4.750   0.1422   0.02457   0.01985  -0.1260   0.7390   0.0549
  -4.500   0.1649   0.02358   0.01879  -0.1254   0.7298   0.0561
  -4.250   0.1790   0.01608   0.01001  -0.1227   0.7224   0.0409
  -4.000   0.2038   0.01527   0.00902  -0.1220   0.7130   0.0414
  -3.750   0.2287   0.01430   0.00785  -0.1213   0.7030   0.0414
  -3.500   0.2540   0.01360   0.00697  -0.1206   0.6933   0.0416
  -3.250   0.2796   0.01301   0.00626  -0.1199   0.6824   0.0420
  -3.000   0.3052   0.01252   0.00566  -0.1193   0.6718   0.0424
  -2.750   0.3307   0.01214   0.00517  -0.1186   0.6610   0.0431
  -2.500   0.3565   0.01183   0.00479  -0.1180   0.6494   0.0441
  -2.250   0.3822   0.01156   0.00442  -0.1174   0.6384   0.0449
  -2.000   0.4077   0.01134   0.00411  -0.1167   0.6277   0.0454
  -1.750   0.4325   0.01091   0.00363  -0.1160   0.6169   0.0464
  -1.500   0.4578   0.01067   0.00336  -0.1153   0.6070   0.0478
  -1.250   0.4832   0.01055   0.00318  -0.1147   0.5975   0.0493
  -1.000   0.5093   0.01044   0.00304  -0.1142   0.5883   0.0512
  -0.750   0.5349   0.01038   0.00290  -0.1136   0.5801   0.0538
  -0.500   0.5609   0.01024   0.00277  -0.1131   0.5719   0.0579
  -0.250   0.5866   0.01021   0.00267  -0.1126   0.5646   0.0640
   0.000   0.6125   0.01002   0.00260  -0.1121   0.5575   0.0954
   0.250   0.6359   0.00960   0.00265  -0.1114   0.5506   0.2672
   0.500   0.6595   0.00927   0.00275  -0.1107   0.5444   0.4303
   0.750   0.6732   0.00837   0.00288  -0.1078   0.5384   0.7861
   1.000   0.7500   0.00830   0.00297  -0.1182   0.5303   1.0000
   1.250   0.7749   0.00839   0.00302  -0.1175   0.5244   1.0000
   1.500   0.7993   0.00853   0.00307  -0.1167   0.5184   1.0000
   1.750   0.8238   0.00867   0.00314  -0.1160   0.5126   1.0000
   2.000   0.8488   0.00877   0.00321  -0.1153   0.5067   1.0000
   2.250   0.8731   0.00893   0.00328  -0.1145   0.5009   1.0000
   2.500   0.8979   0.00906   0.00337  -0.1138   0.4953   1.0000
   2.750   0.9227   0.00917   0.00346  -0.1132   0.4892   1.0000
   3.000   0.9468   0.00934   0.00355  -0.1124   0.4833   1.0000
   3.250   0.9716   0.00945   0.00365  -0.1118   0.4773   1.0000
   3.500   0.9961   0.00958   0.00375  -0.1110   0.4710   1.0000
   3.750   1.0200   0.00977   0.00387  -0.1103   0.4651   1.0000
   4.000   1.0448   0.00986   0.00398  -0.1097   0.4590   1.0000
   4.250   1.0688   0.01002   0.00411  -0.1089   0.4529   1.0000
   4.500   1.0929   0.01019   0.00425  -0.1082   0.4473   1.0000
   4.750   1.1173   0.01031   0.00438  -0.1075   0.4411   1.0000
   5.000   1.1406   0.01050   0.00453  -0.1067   0.4352   1.0000
   5.250   1.1646   0.01065   0.00469  -0.1060   0.4294   1.0000
   5.500   1.1881   0.01081   0.00485  -0.1052   0.4228   1.0000
   5.750   1.2106   0.01103   0.00503  -0.1042   0.4165   1.0000
   6.000   1.2341   0.01117   0.00520  -0.1034   0.4093   1.0000
   6.250   1.2551   0.01141   0.00539  -0.1022   0.4014   1.0000
   6.500   1.2779   0.01157   0.00558  -0.1013   0.3932   1.0000
   6.750   1.2983   0.01183   0.00580  -0.1001   0.3857   1.0000
   7.000   1.3207   0.01201   0.00602  -0.0991   0.3783   1.0000
   7.250   1.3402   0.01230   0.00626  -0.0977   0.3710   1.0000
   7.500   1.3614   0.01250   0.00651  -0.0966   0.3633   1.0000
   8.000   1.3976   0.01304   0.00705  -0.0932   0.3477   1.0000
   8.500   1.4304   0.01367   0.00768  -0.0893   0.3308   1.0000
   8.750   1.4452   0.01407   0.00805  -0.0872   0.3230   1.0000
   9.000   1.4627   0.01439   0.00840  -0.0856   0.3152   1.0000
   9.250   1.4769   0.01483   0.00883  -0.0835   0.3071   1.0000
   9.500   1.4928   0.01523   0.00926  -0.0817   0.2986   1.0000
   9.750   1.5067   0.01572   0.00974  -0.0797   0.2908   1.0000
  10.000   1.5215   0.01620   0.01024  -0.0779   0.2830   1.0000
  10.250   1.5346   0.01676   0.01081  -0.0759   0.2751   1.0000
  10.500   1.5466   0.01739   0.01144  -0.0739   0.2660   1.0000
  10.750   1.5595   0.01801   0.01209  -0.0721   0.2573   1.0000
  11.000   1.5684   0.01886   0.01291  -0.0699   0.2482   1.0000
  11.250   1.5812   0.01956   0.01365  -0.0682   0.2393   1.0000
  11.500   1.5902   0.02049   0.01458  -0.0663   0.2294   1.0000
  11.750   1.5979   0.02154   0.01562  -0.0643   0.2205   1.0000
  12.000   1.6080   0.02251   0.01662  -0.0626   0.2112   1.0000
  12.250   1.6149   0.02372   0.01783  -0.0608   0.2029   1.0000
  12.500   1.6215   0.02500   0.01912  -0.0591   0.1932   1.0000
  12.750   1.6264   0.02647   0.02059  -0.0574   0.1817   1.0000
  13.000   1.6292   0.02814   0.02226  -0.0557   0.1699   1.0000
  13.250   1.6289   0.03013   0.02422  -0.0540   0.1559   1.0000
  13.500   1.6225   0.03272   0.02673  -0.0521   0.1374   1.0000
  13.750   1.6102   0.03596   0.02985  -0.0502   0.1123   1.0000
  14.000   1.5948   0.03969   0.03349  -0.0486   0.0947   1.0000
  14.250   1.5855   0.04303   0.03683  -0.0474   0.0868   1.0000
  14.500   1.5775   0.04641   0.04025  -0.0466   0.0817   1.0000
  14.750   1.5726   0.04960   0.04351  -0.0461   0.0775   1.0000
  15.000   1.5692   0.05270   0.04669  -0.0457   0.0743   1.0000
  15.250   1.5622   0.05631   0.05036  -0.0454   0.0712   1.0000
  15.500   1.5539   0.06019   0.05431  -0.0454   0.0681   1.0000
  15.750   1.5547   0.06303   0.05725  -0.0454   0.0654   1.0000
  16.000   1.5500   0.06659   0.06088  -0.0455   0.0624   1.0000
  16.250   1.5410   0.07078   0.06513  -0.0459   0.0596   1.0000
  16.500   1.5389   0.07415   0.06859  -0.0462   0.0566   1.0000
  16.750   1.5341   0.07791   0.07242  -0.0467   0.0532   1.0000
  17.000   1.5237   0.08250   0.07705  -0.0474   0.0501   1.0000
  17.250   1.5205   0.08619   0.08082  -0.0480   0.0462   1.0000
  17.500   1.5089   0.09114   0.08580  -0.0491   0.0425   1.0000
  17.750   1.5026   0.09538   0.09011  -0.0500   0.0389   1.0000
  18.000   1.4904   0.10061   0.09537  -0.0514   0.0358   1.0000
  18.250   1.4823   0.10528   0.10012  -0.0527   0.0327   1.0000
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