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GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 414 AIRFOIL (goe414-il)
Reynolds number: 100,000
Max Cl/Cd: 54.64 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe414-il-100000-n5.txt
Download as CSV file: xf-goe414-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 414 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2849   0.09268   0.08810  -0.0671   0.9780   0.0347
  -9.250  -0.2829   0.08651   0.08195  -0.0724   0.9727   0.0348
  -9.000  -0.2857   0.07989   0.07536  -0.0780   0.9652   0.0348
  -8.750  -0.2962   0.07258   0.06809  -0.0842   0.9551   0.0348
  -8.500  -0.3166   0.05869   0.05409  -0.0980   0.9421   0.0346
  -8.250  -0.3373   0.04568   0.04036  -0.1081   0.9299   0.0347
  -8.000  -0.3257   0.04177   0.03614  -0.1100   0.9225   0.0362
  -7.750  -0.2987   0.03974   0.03393  -0.1124   0.9191   0.0384
  -7.500  -0.2905   0.03668   0.03043  -0.1116   0.9094   0.0400
  -7.250  -0.2676   0.03297   0.02605  -0.1132   0.9051   0.0423
  -7.000  -0.2508   0.03071   0.02330  -0.1124   0.8971   0.0449
  -6.750  -0.2220   0.02968   0.02221  -0.1133   0.8923   0.0476
  -6.500  -0.1935   0.02823   0.02044  -0.1139   0.8874   0.0506
  -6.250  -0.1701   0.02684   0.01863  -0.1134   0.8796   0.0544
  -6.000  -0.1369   0.02587   0.01762  -0.1147   0.8755   0.0577
  -5.750  -0.1143   0.02503   0.01659  -0.1138   0.8664   0.0612
  -5.500  -0.0814   0.02398   0.01529  -0.1147   0.8616   0.0668
  -5.250  -0.0576   0.02335   0.01458  -0.1140   0.8526   0.0716
  -5.000  -0.0257   0.02233   0.01333  -0.1146   0.8474   0.0789
  -4.750  -0.0015   0.02175   0.01272  -0.1139   0.8383   0.0871
  -4.500   0.0304   0.02109   0.01195  -0.1146   0.8324   0.1000
  -4.250   0.0549   0.02066   0.01140  -0.1139   0.8226   0.1113
  -4.000   0.0873   0.02012   0.01068  -0.1146   0.8168   0.1225
  -3.750   0.1108   0.01983   0.01035  -0.1138   0.8069   0.1319
  -3.500   0.1417   0.01941   0.00986  -0.1143   0.8012   0.1450
  -3.250   0.1658   0.01918   0.00960  -0.1137   0.7916   0.1582
  -3.000   0.1950   0.01879   0.00915  -0.1139   0.7847   0.1705
  -2.750   0.2209   0.01848   0.00879  -0.1134   0.7756   0.1814
  -2.500   0.2481   0.01814   0.00846  -0.1133   0.7675   0.1942
  -2.250   0.2756   0.01784   0.00817  -0.1131   0.7593   0.2138
  -2.000   0.3017   0.01759   0.00798  -0.1128   0.7505   0.2409
  -1.750   0.3305   0.01730   0.00773  -0.1129   0.7428   0.2775
  -1.500   0.3560   0.01714   0.00762  -0.1124   0.7330   0.3151
  -1.250   0.3847   0.01691   0.00739  -0.1125   0.7248   0.3547
  -1.000   0.4111   0.01672   0.00725  -0.1122   0.7150   0.3966
  -0.750   0.4372   0.01647   0.00713  -0.1119   0.7054   0.4508
  -0.500   0.4633   0.01594   0.00697  -0.1114   0.6972   0.5630
  -0.250   0.5253   0.01514   0.00698  -0.1174   0.6870   1.0000
   0.000   0.5511   0.01522   0.00686  -0.1170   0.6777   1.0000
   0.250   0.5774   0.01529   0.00674  -0.1166   0.6686   1.0000
   0.500   0.6018   0.01543   0.00673  -0.1160   0.6584   1.0000
   0.750   0.6279   0.01554   0.00667  -0.1156   0.6491   1.0000
   1.000   0.6532   0.01568   0.00666  -0.1151   0.6392   1.0000
   1.250   0.6777   0.01586   0.00672  -0.1145   0.6290   1.0000
   1.500   0.7038   0.01602   0.00673  -0.1142   0.6200   1.0000
   1.750   0.7281   0.01622   0.00685  -0.1136   0.6100   1.0000
   2.000   0.7529   0.01643   0.00697  -0.1131   0.6009   1.0000
   2.250   0.7784   0.01664   0.00707  -0.1127   0.5924   1.0000
   2.500   0.8022   0.01689   0.00728  -0.1121   0.5832   1.0000
   2.750   0.8283   0.01711   0.00739  -0.1118   0.5758   1.0000
   3.000   0.8513   0.01738   0.00765  -0.1111   0.5665   1.0000
   3.250   0.8768   0.01762   0.00782  -0.1107   0.5594   1.0000
   3.500   0.9001   0.01791   0.00811  -0.1101   0.5511   1.0000
   3.750   0.9261   0.01816   0.00829  -0.1099   0.5452   1.0000
   4.000   0.9492   0.01849   0.00866  -0.1092   0.5380   1.0000
   4.250   0.9744   0.01876   0.00890  -0.1089   0.5321   1.0000
   4.500   0.9978   0.01909   0.00924  -0.1083   0.5253   1.0000
   4.750   1.0217   0.01938   0.00954  -0.1077   0.5186   1.0000
   5.000   1.0452   0.01969   0.00985  -0.1071   0.5121   1.0000
   5.250   1.0682   0.02001   0.01020  -0.1064   0.5053   1.0000
   5.500   1.0922   0.02031   0.01051  -0.1059   0.4991   1.0000
   5.750   1.1137   0.02066   0.01092  -0.1050   0.4918   1.0000
   6.000   1.1384   0.02095   0.01118  -0.1046   0.4860   1.0000
   6.250   1.1591   0.02137   0.01171  -0.1036   0.4795   1.0000
   6.500   1.1828   0.02174   0.01215  -0.1031   0.4746   1.0000
   6.750   1.2081   0.02211   0.01256  -0.1028   0.4706   1.0000
   7.000   1.2289   0.02260   0.01319  -0.1019   0.4656   1.0000
   7.250   1.2518   0.02303   0.01373  -0.1013   0.4609   1.0000
   7.500   1.2764   0.02340   0.01415  -0.1010   0.4555   1.0000
   7.750   1.2910   0.02381   0.01465  -0.0988   0.4443   1.0000
   8.000   1.3038   0.02420   0.01508  -0.0964   0.4309   1.0000
   8.250   1.3167   0.02463   0.01556  -0.0940   0.4188   1.0000
   8.500   1.3294   0.02508   0.01604  -0.0916   0.4072   1.0000
   8.750   1.3350   0.02559   0.01660  -0.0881   0.3931   1.0000
   9.000   1.3407   0.02621   0.01734  -0.0847   0.3796   1.0000
   9.250   1.3455   0.02696   0.01823  -0.0815   0.3655   1.0000
   9.500   1.3456   0.02793   0.01932  -0.0779   0.3452   1.0000
   9.750   1.3452   0.02910   0.02054  -0.0746   0.3174   1.0000
  10.000   1.3415   0.03063   0.02193  -0.0711   0.2798   1.0000
  10.250   1.3280   0.03304   0.02402  -0.0671   0.2404   1.0000
  10.500   1.3157   0.03581   0.02659  -0.0638   0.2087   1.0000
  10.750   1.3010   0.03909   0.02968  -0.0609   0.1562   1.0000
  11.000   1.2739   0.04374   0.03397  -0.0579   0.1117   1.0000
  11.250   1.2523   0.04830   0.03834  -0.0558   0.0729   1.0000
  11.500   1.2300   0.05325   0.04311  -0.0543   0.0437   1.0000
  11.750   1.2181   0.05740   0.04726  -0.0534   0.0363   1.0000
  12.000   1.2103   0.06126   0.05121  -0.0528   0.0327   1.0000
  12.250   1.2044   0.06504   0.05512  -0.0525   0.0304   1.0000
  12.500   1.1978   0.06900   0.05922  -0.0523   0.0288   1.0000
  12.750   1.1905   0.07315   0.06354  -0.0522   0.0278   1.0000
  13.250   1.1779   0.08153   0.07221  -0.0526   0.0263   1.0000
  13.500   1.1729   0.08564   0.07649  -0.0529   0.0256   1.0000
  13.750   1.1678   0.08983   0.08084  -0.0534   0.0249   1.0000
  14.000   1.1628   0.09404   0.08520  -0.0539   0.0241   1.0000
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