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GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 423 AIRFOIL (goe423-il)
Reynolds number: 500,000
Max Cl/Cd: 105.87 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe423-il-500000.txt
Download as CSV file: xf-goe423-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 423 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2032   0.09897   0.09637  -0.0914   0.9634   0.0560
 -11.500  -0.3242   0.06562   0.06292  -0.1148   0.9542   0.0552
 -11.250  -0.3219   0.06357   0.06090  -0.1145   0.9435   0.0556
 -11.000  -0.4818   0.03930   0.03581  -0.1271   0.9160   0.0515
 -10.750  -0.5009   0.03488   0.03095  -0.1247   0.9044   0.0517
 -10.500  -0.4972   0.03262   0.02844  -0.1229   0.8932   0.0523
 -10.250  -0.4912   0.03036   0.02587  -0.1212   0.8832   0.0529
 -10.000  -0.4827   0.02817   0.02334  -0.1194   0.8727   0.0534
  -9.750  -0.4699   0.02642   0.02128  -0.1179   0.8617   0.0539
  -9.500  -0.4537   0.02505   0.01961  -0.1166   0.8507   0.0544
  -9.250  -0.4352   0.02412   0.01841  -0.1154   0.8381   0.0548
  -9.000  -0.4178   0.02261   0.01663  -0.1143   0.8246   0.0555
  -8.750  -0.3966   0.02135   0.01525  -0.1136   0.8100   0.0561
  -8.500  -0.3742   0.02059   0.01437  -0.1129   0.7928   0.0566
  -8.250  -0.3516   0.01997   0.01359  -0.1121   0.7716   0.0571
  -8.000  -0.3292   0.01942   0.01287  -0.1112   0.7459   0.0577
  -7.750  -0.3070   0.01892   0.01218  -0.1103   0.7155   0.0583
  -7.500  -0.2848   0.01845   0.01149  -0.1094   0.6900   0.0589
  -7.250  -0.2619   0.01802   0.01087  -0.1086   0.6721   0.0596
  -7.000  -0.2382   0.01765   0.01032  -0.1079   0.6593   0.0604
  -6.750  -0.2135   0.01727   0.00980  -0.1074   0.6500   0.0610
  -6.500  -0.1888   0.01695   0.00932  -0.1069   0.6419   0.0615
  -6.250  -0.1634   0.01652   0.00879  -0.1065   0.6356   0.0620
  -6.000  -0.1387   0.01567   0.00789  -0.1061   0.6299   0.0629
  -5.750  -0.1136   0.01526   0.00744  -0.1058   0.6247   0.0637
  -5.500  -0.0879   0.01496   0.00710  -0.1054   0.6200   0.0646
  -5.250  -0.0618   0.01466   0.00679  -0.1052   0.6161   0.0656
  -5.000  -0.0356   0.01442   0.00650  -0.1049   0.6121   0.0667
  -4.750  -0.0096   0.01420   0.00622  -0.1046   0.6082   0.0678
  -4.500   0.0166   0.01402   0.00596  -0.1043   0.6043   0.0687
  -4.250   0.0432   0.01385   0.00574  -0.1041   0.6009   0.0694
  -4.000   0.0679   0.01336   0.00527  -0.1036   0.5980   0.0709
  -3.750   0.0937   0.01310   0.00502  -0.1033   0.5951   0.0723
  -3.500   0.1200   0.01291   0.00483  -0.1030   0.5922   0.0738
  -3.250   0.1465   0.01278   0.00467  -0.1028   0.5895   0.0757
  -3.000   0.1734   0.01270   0.00454  -0.1027   0.5867   0.0774
  -2.750   0.1998   0.01255   0.00435  -0.1025   0.5838   0.0798
  -2.500   0.2261   0.01236   0.00420  -0.1022   0.5820   0.0825
  -2.250   0.2529   0.01223   0.00409  -0.1020   0.5799   0.0857
  -2.000   0.2796   0.01209   0.00397  -0.1019   0.5777   0.0902
  -1.750   0.3065   0.01197   0.00388  -0.1017   0.5755   0.0973
  -1.500   0.3330   0.01182   0.00383  -0.1015   0.5734   0.1140
  -1.250   0.3595   0.01167   0.00380  -0.1014   0.5712   0.1471
  -1.000   0.3864   0.01158   0.00377  -0.1013   0.5690   0.1737
  -0.750   0.4134   0.01150   0.00379  -0.1013   0.5667   0.2097
  -0.500   0.4397   0.01134   0.00386  -0.1012   0.5648   0.2787
  -0.250   0.4641   0.01102   0.00385  -0.1008   0.5634   0.3654
   0.000   0.4850   0.01049   0.00393  -0.0997   0.5618   0.5489
   0.250   0.5084   0.01025   0.00398  -0.0989   0.5601   0.6386
   0.500   0.5293   0.00991   0.00408  -0.0973   0.5584   0.7561
   0.750   0.5549   0.00976   0.00429  -0.0964   0.5568   0.8800
   1.000   0.6000   0.00993   0.00452  -0.0997   0.5550   0.9383
   1.250   0.6431   0.01013   0.00469  -0.1028   0.5532   0.9608
   1.500   0.6928   0.01036   0.00486  -0.1074   0.5513   0.9748
   1.750   0.7458   0.01060   0.00503  -0.1128   0.5494   0.9845
   2.000   0.7905   0.01084   0.00521  -0.1166   0.5475   0.9894
   2.250   0.8328   0.01095   0.00532  -0.1198   0.5462   0.9939
   2.500   0.8799   0.01102   0.00539  -0.1242   0.5449   0.9981
   2.750   0.9146   0.01109   0.00547  -0.1259   0.5433   1.0000
   3.000   0.9375   0.01117   0.00556  -0.1251   0.5416   1.0000
   3.250   0.9604   0.01125   0.00564  -0.1243   0.5397   1.0000
   3.500   0.9829   0.01130   0.00568  -0.1234   0.5369   1.0000
   3.750   1.0051   0.01132   0.00565  -0.1224   0.5332   1.0000
   4.000   1.0284   0.01148   0.00575  -0.1216   0.5288   1.0000
   4.250   1.0466   0.01144   0.00576  -0.1198   0.5251   1.0000
   4.500   1.0663   0.01143   0.00578  -0.1182   0.5209   1.0000
   4.750   1.0873   0.01146   0.00579  -0.1170   0.5174   1.0000
   5.000   1.1095   0.01155   0.00585  -0.1159   0.5144   1.0000
   5.250   1.1322   0.01170   0.00599  -0.1151   0.5109   1.0000
   5.500   1.1499   0.01170   0.00606  -0.1131   0.5072   1.0000
   5.750   1.1692   0.01174   0.00612  -0.1115   0.5032   1.0000
   6.000   1.1889   0.01178   0.00617  -0.1099   0.4994   1.0000
   6.250   1.2103   0.01190   0.00624  -0.1087   0.4951   1.0000
   6.500   1.2265   0.01193   0.00635  -0.1065   0.4904   1.0000
   6.750   1.2436   0.01197   0.00643  -0.1044   0.4853   1.0000
   7.000   1.2606   0.01204   0.00649  -0.1023   0.4800   1.0000
   7.250   1.2766   0.01212   0.00661  -0.1001   0.4737   1.0000
   7.500   1.2903   0.01219   0.00670  -0.0974   0.4654   1.0000
   7.750   1.3022   0.01230   0.00683  -0.0943   0.4564   1.0000
   8.000   1.3135   0.01249   0.00699  -0.0913   0.4454   1.0000
   8.250   1.3251   0.01275   0.00724  -0.0884   0.4289   1.0000
   8.500   1.3313   0.01326   0.00765  -0.0848   0.3979   1.0000
   8.750   1.3203   0.01462   0.00869  -0.0787   0.3428   1.0000
   9.000   1.3075   0.01642   0.01020  -0.0730   0.2950   1.0000
   9.250   1.2957   0.01840   0.01193  -0.0679   0.2513   1.0000
   9.500   1.2813   0.02075   0.01403  -0.0630   0.2063   1.0000
   9.750   1.2566   0.02403   0.01699  -0.0578   0.1470   1.0000
  10.000   1.2327   0.02765   0.02038  -0.0534   0.1027   1.0000
  10.250   1.2134   0.03127   0.02381  -0.0500   0.0631   1.0000
  10.500   1.2113   0.03374   0.02625  -0.0483   0.0545   1.0000
  10.750   1.2135   0.03595   0.02848  -0.0470   0.0510   1.0000
  11.000   1.2180   0.03803   0.03061  -0.0460   0.0489   1.0000
  11.250   1.2233   0.04009   0.03272  -0.0451   0.0474   1.0000
  11.500   1.2272   0.04230   0.03499  -0.0442   0.0461   1.0000
  11.750   1.2294   0.04471   0.03744  -0.0433   0.0450   1.0000
  12.000   1.2297   0.04734   0.04012  -0.0424   0.0441   1.0000
  12.250   1.2327   0.04974   0.04258  -0.0417   0.0434   1.0000
  12.500   1.2374   0.05195   0.04486  -0.0410   0.0428   1.0000
  12.750   1.2409   0.05431   0.04728  -0.0404   0.0422   1.0000
  13.000   1.2442   0.05670   0.04972  -0.0398   0.0416   1.0000
  13.250   1.2469   0.05919   0.05226  -0.0392   0.0410   1.0000
  13.500   1.2491   0.06174   0.05486  -0.0387   0.0404   1.0000
  13.750   1.2505   0.06439   0.05756  -0.0381   0.0398   1.0000
  14.000   1.2506   0.06718   0.06040  -0.0376   0.0392   1.0000
  14.250   1.2492   0.07018   0.06343  -0.0371   0.0387   1.0000
  14.500   1.2469   0.07325   0.06655  -0.0365   0.0383   1.0000
  14.750   1.2514   0.07564   0.06900  -0.0362   0.0380   1.0000
  15.000   1.2565   0.07793   0.07134  -0.0360   0.0376   1.0000
  15.250   1.2613   0.08028   0.07375  -0.0357   0.0373   1.0000
  15.500   1.2657   0.08268   0.07621  -0.0355   0.0369   1.0000
  15.750   1.2708   0.08499   0.07856  -0.0353   0.0365   1.0000
  16.000   1.2764   0.08724   0.08086  -0.0351   0.0360   1.0000
  16.250   1.2813   0.08958   0.08323  -0.0349   0.0355   1.0000
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