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GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 50,000
Max Cl/Cd: 28.17 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe675-il-50000-n5.txt
Download as CSV file: xf-goe675-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 675 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1307   0.12281   0.11596  -0.0589   0.9491   0.1381
  -9.250  -0.1254   0.11991   0.11306  -0.0603   0.9450   0.1401
  -9.000  -0.2392   0.11907   0.11178  -0.0565   0.9651   0.1045
  -8.750  -0.2269   0.11563   0.10833  -0.0577   0.9606   0.1020
  -8.250  -0.2434   0.10760   0.10031  -0.0640   0.9479   0.0946
  -8.000  -0.2362   0.10441   0.09712  -0.0657   0.9429   0.0942
  -7.750  -0.2310   0.10134   0.09405  -0.0671   0.9379   0.0936
  -7.500  -0.2358   0.09884   0.09160  -0.0667   0.9303   0.0929
  -7.250  -0.2297   0.09500   0.08774  -0.0700   0.9248   0.0922
  -7.000  -0.2321   0.09165   0.08440  -0.0715   0.9175   0.0916
  -6.750  -0.2318   0.08774   0.08048  -0.0742   0.9102   0.0917
  -6.500  -0.2217   0.08235   0.07500  -0.0806   0.9052   0.0927
  -6.250  -0.2281   0.07828   0.07087  -0.0822   0.8964   0.0933
  -6.000  -0.2200   0.07128   0.06360  -0.0891   0.8902   0.0943
  -5.750  -0.1987   0.06595   0.05803  -0.0945   0.8864   0.0956
  -5.500  -0.1938   0.06415   0.05616  -0.0932   0.8786   0.0968
  -5.250  -0.1742   0.06165   0.05351  -0.0949   0.8731   0.0995
  -5.000  -0.1454   0.05574   0.04695  -0.1013   0.8692   0.1046
  -4.750  -0.1242   0.05350   0.04449  -0.1025   0.8639   0.1078
  -4.500  -0.1066   0.05235   0.04324  -0.1022   0.8569   0.1115
  -4.250  -0.0734   0.04895   0.03913  -0.1060   0.8525   0.1188
  -4.000  -0.0384   0.04821   0.03842  -0.1077   0.8487   0.1241
  -3.750  -0.0210   0.04661   0.03631  -0.1074   0.8390   0.1307
  -3.500   0.0133   0.04560   0.03527  -0.1090   0.8330   0.1365
  -3.250   0.0434   0.04442   0.03377  -0.1099   0.8255   0.1432
  -3.000   0.0719   0.04325   0.03229  -0.1106   0.8173   0.1488
  -2.750   0.1115   0.04220   0.03113  -0.1126   0.8125   0.1546
  -2.500   0.1297   0.04172   0.03043  -0.1114   0.8026   0.1593
  -2.250   0.1654   0.04072   0.02910  -0.1128   0.7969   0.1640
  -2.000   0.1973   0.04008   0.02845  -0.1135   0.7910   0.1689
  -1.750   0.2181   0.03982   0.02810  -0.1126   0.7815   0.1738
  -1.500   0.2573   0.03899   0.02700  -0.1141   0.7769   0.1796
  -1.250   0.2742   0.03891   0.02693  -0.1125   0.7663   0.1835
  -1.000   0.3086   0.03834   0.02633  -0.1133   0.7606   0.1909
  -0.750   0.3319   0.03825   0.02608  -0.1125   0.7512   0.1979
  -0.500   0.3634   0.03778   0.02564  -0.1128   0.7440   0.2053
  -0.250   0.3948   0.03739   0.02515  -0.1130   0.7371   0.2164
   0.000   0.4180   0.03729   0.02514  -0.1122   0.7271   0.2280
   0.250   0.4574   0.03645   0.02433  -0.1133   0.7229   0.2481
   0.500   0.4729   0.03672   0.02469  -0.1116   0.7099   0.2666
   0.750   0.5115   0.03575   0.02389  -0.1126   0.7055   0.3109
   1.000   0.5276   0.03589   0.02433  -0.1112   0.6926   0.3625
   1.250   0.5610   0.03422   0.02368  -0.1110   0.6883   0.5764
   1.750   0.6104   0.03338   0.02306  -0.1083   0.6701   1.0000
   2.000   0.6253   0.03404   0.02357  -0.1065   0.6566   1.0000
   2.250   0.6640   0.03342   0.02274  -0.1072   0.6520   1.0000
   2.500   0.6781   0.03415   0.02336  -0.1054   0.6383   1.0000
   2.750   0.7173   0.03348   0.02251  -0.1061   0.6338   1.0000
   3.000   0.7302   0.03434   0.02329  -0.1043   0.6201   1.0000
   3.250   0.7692   0.03369   0.02248  -0.1050   0.6155   1.0000
   3.500   0.7816   0.03463   0.02336  -0.1031   0.6021   1.0000
   4.000   0.8315   0.03508   0.02364  -0.1019   0.5845   1.0000
   4.250   0.8716   0.03440   0.02284  -0.1027   0.5799   1.0000
   4.500   0.8800   0.03571   0.02413  -0.1006   0.5672   1.0000
   4.750   0.9193   0.03509   0.02341  -0.1013   0.5624   1.0000
   5.000   0.9263   0.03655   0.02487  -0.0992   0.5506   1.0000
   5.250   0.9637   0.03608   0.02431  -0.0998   0.5455   1.0000
   5.500   0.9711   0.03757   0.02582  -0.0977   0.5347   1.0000
   5.750   1.0047   0.03735   0.02554  -0.0980   0.5290   1.0000
   6.000   1.0168   0.03859   0.02680  -0.0964   0.5201   1.0000
   6.250   1.0421   0.03895   0.02713  -0.0959   0.5132   1.0000
   6.500   1.0821   0.03841   0.02651  -0.0968   0.5086   1.0000
   6.750   1.0771   0.04078   0.02899  -0.0938   0.4982   1.0000
   7.000   1.1127   0.04050   0.02865  -0.0942   0.4932   1.0000
   7.250   1.1157   0.04243   0.03066  -0.0920   0.4846   1.0000
   7.500   1.1376   0.04307   0.03132  -0.0913   0.4780   1.0000
   7.750   1.1802   0.04237   0.03057  -0.0924   0.4739   1.0000
   8.000   1.1606   0.04591   0.03427  -0.0885   0.4637   1.0000
   8.250   1.1928   0.04579   0.03417  -0.0885   0.4584   1.0000
   8.500   1.2122   0.04668   0.03509  -0.0877   0.4525   1.0000
   8.750   1.1990   0.04999   0.03853  -0.0847   0.4432   1.0000
   9.000   1.2403   0.04912   0.03765  -0.0852   0.4389   1.0000
   9.250   1.2061   0.05438   0.04309  -0.0814   0.4286   1.0000
   9.500   1.2274   0.05499   0.04376  -0.0806   0.4228   1.0000
   9.750   1.2779   0.05323   0.04198  -0.0815   0.4193   1.0000
  10.000   1.2038   0.06263   0.05162  -0.0767   0.4056   1.0000
  10.250   1.2447   0.06119   0.05020  -0.0765   0.4022   1.0000
  10.500   1.3023   0.05851   0.04754  -0.0772   0.3996   1.0000
  10.750   1.2051   0.07113   0.06037  -0.0732   0.3838   1.0000
  11.000   1.2524   0.06869   0.05799  -0.0727   0.3817   1.0000
  11.500   1.2018   0.08072   0.07023  -0.0707   0.3623   1.0000
  12.000   1.0991   0.10239   0.09211  -0.0730   0.3324   1.0000
  12.250   1.1229   0.10218   0.09199  -0.0719   0.3293   1.0000
  12.750   1.1072   0.11170   0.10167  -0.0728   0.3128   1.0000
  13.250   1.0935   0.12112   0.11124  -0.0743   0.2971   1.0000
  13.500   1.1193   0.12048   0.11069  -0.0730   0.2945   1.0000
  14.000   1.1078   0.12962   0.12000  -0.0749   0.2792   1.0000
  14.500   1.1021   0.13779   0.12833  -0.0768   0.2644   1.0000
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