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GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 480 AIRFOIL (goe480-il)
Reynolds number: 200,000
Max Cl/Cd: 79.21 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe480-il-200000-n5.txt
Download as CSV file: xf-goe480-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 480 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2723   0.11693   0.11308  -0.0445   1.0000   0.0376
 -11.000  -0.2763   0.11360   0.10979  -0.0451   1.0000   0.0380
 -10.750  -0.2762   0.11132   0.10756  -0.0446   1.0000   0.0389
 -10.500  -0.2612   0.10855   0.10480  -0.0467   0.9975   0.0396
 -10.250  -0.2441   0.10546   0.10171  -0.0500   0.9909   0.0414
 -10.000  -0.2315   0.10132   0.09755  -0.0542   0.9843   0.0423
  -9.750  -0.2214   0.09698   0.09320  -0.0584   0.9756   0.0430
  -9.500  -0.2150   0.09191   0.08812  -0.0643   0.9660   0.0449
  -9.250  -0.1891   0.09021   0.08641  -0.0660   0.9599   0.0466
  -9.000  -0.1720   0.08653   0.08270  -0.0705   0.9508   0.0476
  -8.750  -0.1559   0.08216   0.07830  -0.0759   0.9406   0.0477
  -8.500  -0.1387   0.07782   0.07392  -0.0818   0.9292   0.0485
  -8.250  -0.1235   0.07300   0.06904  -0.0888   0.9148   0.0497
  -8.000  -0.1140   0.06799   0.06396  -0.0955   0.8967   0.0502
  -7.750  -0.1099   0.06239   0.05826  -0.1027   0.8779   0.0507
  -7.500  -0.1124   0.05421   0.04990  -0.1123   0.8596   0.0519
  -7.250  -0.0924   0.05371   0.04935  -0.1117   0.8497   0.0526
  -7.000  -0.0826   0.04968   0.04518  -0.1148   0.8374   0.0528
  -6.750  -0.0723   0.04527   0.04060  -0.1178   0.8269   0.0531
  -6.500  -0.0573   0.04218   0.03732  -0.1194   0.8178   0.0537
  -6.250  -0.0416   0.03941   0.03438  -0.1205   0.8091   0.0547
  -6.000  -0.0285   0.03471   0.02932  -0.1221   0.8010   0.0552
  -5.750  -0.0141   0.03067   0.02486  -0.1227   0.7935   0.0556
  -5.500   0.0038   0.02789   0.02168  -0.1227   0.7862   0.0562
  -5.250   0.0247   0.02586   0.01927  -0.1225   0.7801   0.0573
  -5.000   0.0458   0.02416   0.01724  -0.1220   0.7729   0.0580
  -4.750   0.0688   0.02274   0.01549  -0.1215   0.7666   0.0584
  -4.500   0.0927   0.02159   0.01405  -0.1210   0.7606   0.0588
  -4.250   0.1168   0.02064   0.01286  -0.1205   0.7538   0.0592
  -4.000   0.1422   0.01984   0.01181  -0.1200   0.7480   0.0596
  -3.750   0.1676   0.01925   0.01101  -0.1195   0.7418   0.0601
  -3.500   0.1926   0.01844   0.01003  -0.1190   0.7352   0.0609
  -3.250   0.2185   0.01771   0.00918  -0.1187   0.7297   0.0617
  -3.000   0.2441   0.01715   0.00856  -0.1183   0.7232   0.0623
  -2.750   0.2700   0.01667   0.00800  -0.1178   0.7167   0.0628
  -2.500   0.2968   0.01625   0.00747  -0.1175   0.7112   0.0634
  -2.250   0.3225   0.01587   0.00706  -0.1169   0.7042   0.0641
  -2.000   0.3487   0.01552   0.00665  -0.1165   0.6977   0.0648
  -1.750   0.3753   0.01521   0.00627  -0.1161   0.6919   0.0655
  -1.500   0.4010   0.01492   0.00598  -0.1155   0.6845   0.0664
  -1.250   0.4274   0.01469   0.00570  -0.1151   0.6781   0.0678
  -1.000   0.4534   0.01449   0.00547  -0.1146   0.6713   0.0691
  -0.750   0.4793   0.01429   0.00525  -0.1140   0.6638   0.0701
  -0.500   0.5056   0.01412   0.00503  -0.1136   0.6574   0.0709
  -0.250   0.5309   0.01392   0.00485  -0.1129   0.6493   0.0718
   0.000   0.5566   0.01371   0.00462  -0.1124   0.6423   0.0733
   0.250   0.5820   0.01357   0.00451  -0.1118   0.6344   0.0749
   0.500   0.6078   0.01347   0.00439  -0.1113   0.6266   0.0768
   0.750   0.6334   0.01341   0.00432  -0.1107   0.6186   0.0792
   1.000   0.6590   0.01336   0.00425  -0.1101   0.6103   0.0827
   1.250   0.6844   0.01331   0.00421  -0.1095   0.6019   0.0878
   1.500   0.7097   0.01326   0.00418  -0.1088   0.5933   0.0958
   1.750   0.7345   0.01315   0.00423  -0.1082   0.5846   0.1342
   2.000   0.7591   0.01306   0.00429  -0.1075   0.5759   0.2039
   2.250   0.7816   0.01272   0.00442  -0.1066   0.5671   0.3691
   2.750   0.8618   0.01178   0.00467  -0.1117   0.5466   1.0000
   3.000   0.8856   0.01195   0.00474  -0.1108   0.5376   1.0000
   3.250   0.9093   0.01213   0.00486  -0.1098   0.5281   1.0000
   3.500   0.9329   0.01232   0.00498  -0.1089   0.5191   1.0000
   3.750   0.9564   0.01251   0.00511  -0.1080   0.5100   1.0000
   4.000   0.9799   0.01271   0.00527  -0.1071   0.5015   1.0000
   4.250   1.0031   0.01293   0.00543  -0.1061   0.4928   1.0000
   4.500   1.0262   0.01314   0.00562  -0.1052   0.4842   1.0000
   4.750   1.0489   0.01338   0.00581  -0.1042   0.4752   1.0000
   5.000   1.0718   0.01361   0.00602  -0.1032   0.4668   1.0000
   5.250   1.0941   0.01386   0.00625  -0.1021   0.4582   1.0000
   5.500   1.1165   0.01410   0.00649  -0.1011   0.4497   1.0000
   5.750   1.1379   0.01438   0.00673  -0.0999   0.4406   1.0000
   6.000   1.1597   0.01464   0.00700  -0.0988   0.4318   1.0000
   6.250   1.1807   0.01493   0.00728  -0.0975   0.4236   1.0000
   6.500   1.2019   0.01521   0.00758  -0.0963   0.4151   1.0000
   6.750   1.2217   0.01554   0.00788  -0.0949   0.4063   1.0000
   7.000   1.2415   0.01584   0.00821  -0.0935   0.3964   1.0000
   7.250   1.2595   0.01620   0.00855  -0.0918   0.3863   1.0000
   7.500   1.2771   0.01655   0.00891  -0.0900   0.3755   1.0000
   7.750   1.2941   0.01693   0.00929  -0.0882   0.3650   1.0000
   8.000   1.3080   0.01734   0.00967  -0.0858   0.3548   1.0000
   8.250   1.3228   0.01774   0.01010  -0.0836   0.3444   1.0000
   8.500   1.3367   0.01819   0.01056  -0.0813   0.3352   1.0000
   8.750   1.3502   0.01867   0.01105  -0.0790   0.3256   1.0000
   9.000   1.3637   0.01917   0.01157  -0.0768   0.3160   1.0000
   9.500   1.3872   0.02036   0.01279  -0.0721   0.2951   1.0000
   9.750   1.3971   0.02107   0.01349  -0.0697   0.2831   1.0000
  10.000   1.4054   0.02188   0.01428  -0.0672   0.2706   1.0000
  10.250   1.4122   0.02282   0.01519  -0.0646   0.2571   1.0000
  10.500   1.4193   0.02381   0.01618  -0.0623   0.2438   1.0000
  10.750   1.4282   0.02478   0.01718  -0.0603   0.2322   1.0000
  11.000   1.4352   0.02591   0.01831  -0.0582   0.2203   1.0000
  11.250   1.4407   0.02718   0.01958  -0.0561   0.2079   1.0000
  11.500   1.4451   0.02860   0.02099  -0.0542   0.1945   1.0000
  11.750   1.4484   0.03018   0.02255  -0.0523   0.1789   1.0000
  12.000   1.4492   0.03202   0.02437  -0.0504   0.1600   1.0000
  12.250   1.4458   0.03429   0.02655  -0.0485   0.1385   1.0000
  12.500   1.4399   0.03690   0.02906  -0.0467   0.1165   1.0000
  12.750   1.4326   0.03976   0.03182  -0.0451   0.0990   1.0000
  13.000   1.4272   0.04258   0.03461  -0.0438   0.0874   1.0000
  13.250   1.4243   0.04527   0.03732  -0.0427   0.0797   1.0000
  13.500   1.4207   0.04815   0.04023  -0.0418   0.0736   1.0000
  13.750   1.4186   0.05097   0.04312  -0.0412   0.0685   1.0000
  14.000   1.4144   0.05413   0.04634  -0.0406   0.0644   1.0000
  14.250   1.4136   0.05702   0.04932  -0.0403   0.0605   1.0000
  14.500   1.4095   0.06040   0.05276  -0.0401   0.0572   1.0000
  14.750   1.4060   0.06378   0.05623  -0.0401   0.0542   1.0000
  15.000   1.4041   0.06709   0.05964  -0.0402   0.0511   1.0000
  15.250   1.3992   0.07086   0.06349  -0.0405   0.0485   1.0000
  15.500   1.3951   0.07461   0.06732  -0.0409   0.0461   1.0000
  15.750   1.3925   0.07822   0.07105  -0.0414   0.0437   1.0000
  16.000   1.3879   0.08219   0.07511  -0.0421   0.0416   1.0000
  16.250   1.3812   0.08656   0.07954  -0.0430   0.0399   1.0000
  16.500   1.3783   0.09040   0.08350  -0.0438   0.0381   1.0000
  16.750   1.3747   0.09440   0.08761  -0.0448   0.0365   1.0000
  17.000   1.3702   0.09862   0.09190  -0.0459   0.0350   1.0000
  17.250   1.3639   0.10317   0.09651  -0.0472   0.0338   1.0000
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