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GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 508 AIRFOIL (goe508-il)
Reynolds number: 200,000
Max Cl/Cd: 69.56 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe508-il-200000-n5.txt
Download as CSV file: xf-goe508-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 508 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  -0.0098   0.09273   0.08814  -0.1133   0.8561   0.0401
 -11.000  -0.0074   0.08863   0.08397  -0.1158   0.8468   0.0405
 -10.750  -0.0074   0.08472   0.08001  -0.1176   0.8373   0.0406
 -10.500  -0.0095   0.08051   0.07575  -0.1196   0.8294   0.0406
 -10.000  -0.2485   0.04059   0.03532  -0.1394   0.8064   0.0396
  -9.750  -0.2880   0.03662   0.03095  -0.1351   0.7974   0.0397
  -9.500  -0.2995   0.03376   0.02769  -0.1322   0.7911   0.0400
  -9.250  -0.3015   0.03148   0.02507  -0.1296   0.7841   0.0404
  -9.000  -0.2967   0.02955   0.02275  -0.1274   0.7782   0.0410
  -8.750  -0.2878   0.02783   0.02056  -0.1254   0.7734   0.0416
  -8.500  -0.2717   0.02678   0.01941  -0.1240   0.7675   0.0420
  -8.250  -0.2530   0.02595   0.01850  -0.1229   0.7616   0.0425
  -8.000  -0.2331   0.02515   0.01756  -0.1219   0.7566   0.0430
  -7.750  -0.2133   0.02433   0.01661  -0.1208   0.7514   0.0435
  -7.500  -0.1935   0.02352   0.01568  -0.1197   0.7456   0.0440
  -7.250  -0.1724   0.02273   0.01472  -0.1187   0.7405   0.0446
  -7.000  -0.1500   0.02196   0.01375  -0.1178   0.7362   0.0454
  -6.750  -0.1285   0.02127   0.01292  -0.1168   0.7305   0.0461
  -6.500  -0.1059   0.02065   0.01212  -0.1158   0.7248   0.0469
  -6.250  -0.0824   0.02006   0.01151  -0.1151   0.7198   0.0477
  -6.000  -0.0588   0.01961   0.01103  -0.1144   0.7147   0.0488
  -5.750  -0.0357   0.01916   0.01054  -0.1136   0.7089   0.0498
  -5.500  -0.0115   0.01870   0.00998  -0.1128   0.7038   0.0511
  -5.250   0.0135   0.01825   0.00939  -0.1122   0.6996   0.0523
  -5.000   0.0365   0.01781   0.00895  -0.1113   0.6938   0.0534
  -4.750   0.0602   0.01743   0.00856  -0.1105   0.6882   0.0546
  -4.500   0.0850   0.01709   0.00816  -0.1099   0.6832   0.0563
  -4.250   0.1094   0.01679   0.00780  -0.1092   0.6779   0.0584
  -4.000   0.1329   0.01647   0.00750  -0.1083   0.6721   0.0605
  -3.750   0.1577   0.01621   0.00720  -0.1077   0.6672   0.0630
  -3.500   0.1832   0.01596   0.00687  -0.1071   0.6631   0.0659
  -3.250   0.2068   0.01573   0.00670  -0.1063   0.6574   0.0689
  -3.000   0.2315   0.01555   0.00650  -0.1056   0.6522   0.0733
  -2.750   0.2570   0.01538   0.00632  -0.1050   0.6475   0.0787
  -2.500   0.2818   0.01523   0.00619  -0.1044   0.6425   0.0857
  -2.250   0.3063   0.01511   0.00609  -0.1037   0.6370   0.0948
  -2.000   0.3316   0.01500   0.00596  -0.1031   0.6324   0.1051
  -1.750   0.3579   0.01490   0.00581  -0.1027   0.6286   0.1162
  -1.500   0.3819   0.01480   0.00577  -0.1019   0.6237   0.1271
  -1.250   0.4063   0.01471   0.00571  -0.1012   0.6188   0.1381
  -1.000   0.4315   0.01462   0.00562  -0.1007   0.6143   0.1502
  -0.750   0.4575   0.01455   0.00553  -0.1002   0.6104   0.1642
  -0.500   0.4807   0.01448   0.00555  -0.0993   0.6052   0.1815
  -0.250   0.5044   0.01437   0.00554  -0.0985   0.6000   0.2080
   0.000   0.5285   0.01421   0.00548  -0.0978   0.5952   0.2514
   0.500   0.5691   0.01365   0.00554  -0.0951   0.5842   0.4292
   0.750   0.5853   0.01315   0.00560  -0.0927   0.5795   0.6009
   1.000   0.6129   0.01275   0.00575  -0.0920   0.5753   0.7995
   1.250   0.6901   0.01287   0.00603  -0.1018   0.5694   0.9230
   1.500   0.7382   0.01302   0.00610  -0.1059   0.5637   0.9564
   1.750   0.7803   0.01318   0.00613  -0.1088   0.5590   0.9767
   2.000   0.8278   0.01335   0.00626  -0.1130   0.5528   0.9954
   2.250   0.8589   0.01348   0.00632  -0.1138   0.5466   1.0000
   2.500   0.8788   0.01361   0.00634  -0.1123   0.5415   1.0000
   2.750   0.8964   0.01375   0.00646  -0.1104   0.5356   1.0000
   3.000   0.9144   0.01389   0.00656  -0.1085   0.5294   1.0000
   3.250   0.9342   0.01404   0.00663  -0.1069   0.5246   1.0000
   3.500   0.9532   0.01420   0.00676  -0.1053   0.5202   1.0000
   3.750   0.9713   0.01437   0.00693  -0.1035   0.5152   1.0000
   4.000   0.9901   0.01454   0.00706  -0.1018   0.5103   1.0000
   4.250   1.0100   0.01471   0.00717  -0.1003   0.5058   1.0000
   4.500   1.0269   0.01490   0.00738  -0.0983   0.5006   1.0000
   4.750   1.0439   0.01509   0.00756  -0.0962   0.4949   1.0000
   5.000   1.0616   0.01527   0.00770  -0.0943   0.4894   1.0000
   5.250   1.0768   0.01548   0.00791  -0.0920   0.4832   1.0000
   5.500   1.0910   0.01570   0.00813  -0.0895   0.4764   1.0000
   5.750   1.1049   0.01591   0.00829  -0.0870   0.4701   1.0000
   6.000   1.1152   0.01614   0.00856  -0.0838   0.4630   1.0000
   6.250   1.1268   0.01640   0.00879  -0.0809   0.4557   1.0000
   6.500   1.1384   0.01669   0.00909  -0.0781   0.4479   1.0000
   6.750   1.1496   0.01701   0.00940  -0.0753   0.4391   1.0000
   7.000   1.1607   0.01739   0.00978  -0.0727   0.4294   1.0000
   7.250   1.1704   0.01782   0.01018  -0.0699   0.4189   1.0000
   7.500   1.1796   0.01833   0.01068  -0.0671   0.4062   1.0000
   7.750   1.1876   0.01893   0.01124  -0.0644   0.3923   1.0000
   8.000   1.1935   0.01967   0.01191  -0.0614   0.3767   1.0000
   8.250   1.1976   0.02056   0.01273  -0.0585   0.3601   1.0000
   8.500   1.2010   0.02159   0.01367  -0.0556   0.3441   1.0000
   8.750   1.2037   0.02275   0.01475  -0.0529   0.3287   1.0000
   9.000   1.2082   0.02392   0.01585  -0.0505   0.3164   1.0000
   9.250   1.2110   0.02524   0.01709  -0.0481   0.3043   1.0000
   9.500   1.2152   0.02656   0.01836  -0.0460   0.2933   1.0000
   9.750   1.2210   0.02785   0.01961  -0.0442   0.2840   1.0000
  10.000   1.2255   0.02925   0.02095  -0.0423   0.2754   1.0000
  10.250   1.2335   0.03049   0.02218  -0.0409   0.2683   1.0000
  10.500   1.2420   0.03172   0.02340  -0.0395   0.2625   1.0000
  10.750   1.2496   0.03303   0.02468  -0.0381   0.2577   1.0000
  11.000   1.2606   0.03415   0.02583  -0.0371   0.2532   1.0000
  11.250   1.2716   0.03529   0.02701  -0.0360   0.2491   1.0000
  11.500   1.2813   0.03653   0.02825  -0.0350   0.2450   1.0000
  11.750   1.2902   0.03785   0.02955  -0.0339   0.2413   1.0000
  12.000   1.3013   0.03903   0.03076  -0.0330   0.2378   1.0000
  12.250   1.3127   0.04023   0.03202  -0.0322   0.2341   1.0000
  12.500   1.3237   0.04146   0.03330  -0.0314   0.2309   1.0000
  12.750   1.3332   0.04282   0.03468  -0.0306   0.2273   1.0000
  13.000   1.3429   0.04415   0.03600  -0.0298   0.2244   1.0000
  13.250   1.3543   0.04538   0.03727  -0.0290   0.2218   1.0000
  13.500   1.3657   0.04666   0.03865  -0.0285   0.2189   1.0000
  13.750   1.3758   0.04807   0.04014  -0.0279   0.2158   1.0000
  14.000   1.3852   0.04953   0.04165  -0.0273   0.2126   1.0000
  14.250   1.3940   0.05104   0.04319  -0.0267   0.2096   1.0000
  14.500   1.4033   0.05249   0.04462  -0.0260   0.2068   1.0000
  14.750   1.4131   0.05398   0.04623  -0.0256   0.2043   1.0000
  15.000   1.4217   0.05563   0.04799  -0.0252   0.2013   1.0000
  15.250   1.4291   0.05740   0.04985  -0.0248   0.1979   1.0000
  15.500   1.4355   0.05927   0.05177  -0.0244   0.1945   1.0000
  15.750   1.4410   0.06118   0.05368  -0.0240   0.1911   1.0000
  16.000   1.4451   0.06345   0.05610  -0.0239   0.1865   1.0000
  16.250   1.4485   0.06577   0.05851  -0.0237   0.1818   1.0000
  16.500   1.4498   0.06832   0.06108  -0.0236   0.1772   1.0000
  16.750   1.4535   0.07068   0.06357  -0.0236   0.1726   1.0000
  17.000   1.4558   0.07322   0.06620  -0.0236   0.1680   1.0000
  17.250   1.4563   0.07595   0.06898  -0.0236   0.1637   1.0000
  17.500   1.4584   0.07857   0.07170  -0.0237   0.1591   1.0000
  17.750   1.4578   0.08153   0.07474  -0.0240   0.1535   1.0000
  18.000   1.4558   0.08470   0.07795  -0.0243   0.1487   1.0000
  18.250   1.4545   0.08782   0.08116  -0.0246   0.1434   1.0000
  18.500   1.4494   0.09143   0.08480  -0.0251   0.1383   1.0000
  18.750   1.4470   0.09474   0.08820  -0.0256   0.1337   1.0000
  19.000   1.4420   0.09843   0.09195  -0.0263   0.1289   1.0000
  19.250   1.4361   0.10227   0.09583  -0.0271   0.1249   1.0000
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