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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 50,000
Max Cl/Cd: 37.94 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe377-il-50000.txt
Download as CSV file: xf-goe377-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3833   0.10730   0.10040  -0.0210   1.0000   0.1272
  -8.250  -0.3917   0.10633   0.09957  -0.0224   1.0000   0.1314
  -8.000  -0.4046   0.10593   0.09932  -0.0236   1.0000   0.1323
  -7.750  -0.3838   0.09959   0.09297  -0.0212   1.0000   0.1429
  -7.500  -0.3950   0.09866   0.09218  -0.0221   1.0000   0.1456
  -7.250  -0.3876   0.09444   0.08798  -0.0205   1.0000   0.1520
  -7.000  -0.3907   0.09254   0.08618  -0.0214   1.0000   0.1589
  -6.750  -0.3901   0.08937   0.08310  -0.0213   1.0000   0.1643
  -6.500  -0.3887   0.08695   0.08075  -0.0213   1.0000   0.1728
  -6.000  -0.3884   0.08221   0.07613  -0.0228   1.0000   0.1887
  -5.750  -0.3820   0.07822   0.07221  -0.0197   1.0000   0.1971
  -5.500  -0.3805   0.07555   0.06960  -0.0198   1.0000   0.2072
  -5.250  -0.3777   0.07284   0.06693  -0.0195   1.0000   0.2204
  -5.000  -0.3738   0.06995   0.06408  -0.0181   1.0000   0.2355
  -4.750  -0.3696   0.06716   0.06132  -0.0164   1.0000   0.2541
  -4.500   0.0083   0.03956   0.03261  -0.0296   1.0000   1.0000
  -4.250  -0.0002   0.03896   0.03213  -0.0256   1.0000   0.9923
  -3.250  -0.3769   0.05130   0.04604   0.0140   1.0000   0.5084
  -3.000  -0.3816   0.04894   0.04378   0.0209   1.0000   0.5593
  -2.750  -0.3835   0.04636   0.04132   0.0289   1.0000   0.6052
  -2.500  -0.3827   0.04400   0.03903   0.0335   1.0000   0.6421
  -2.250  -0.3772   0.04136   0.03644   0.0368   1.0000   0.6703
  -2.000  -0.1570   0.03619   0.02835  -0.0288   1.0000   0.2578
  -1.750  -0.1142   0.03348   0.02466  -0.0309   1.0000   0.1870
  -1.500  -0.0857   0.03162   0.02218  -0.0307   1.0000   0.1738
  -1.250  -0.0611   0.03005   0.02027  -0.0301   1.0000   0.1728
  -1.000  -0.0360   0.02857   0.01843  -0.0295   1.0000   0.1675
  -0.750  -0.0103   0.02743   0.01689  -0.0290   1.0000   0.1653
  -0.500   0.0122   0.02662   0.01583  -0.0282   1.0000   0.1707
  -0.250   0.0344   0.02597   0.01496  -0.0274   1.0000   0.1788
   0.000   0.0621   0.02544   0.01415  -0.0275   1.0000   0.1845
   0.250   0.0881   0.02503   0.01358  -0.0274   1.0000   0.1930
   0.500   0.1114   0.02474   0.01327  -0.0271   1.0000   0.2080
   0.750   0.1334   0.02451   0.01316  -0.0269   1.0000   0.2421
   1.000   0.1743   0.02214   0.01264  -0.0295   1.0000   1.0000
   1.250   0.1913   0.02287   0.01285  -0.0286   1.0000   1.0000
   1.500   0.2120   0.02374   0.01345  -0.0291   0.9978   1.0000
   1.750   0.2754   0.02516   0.01456  -0.0374   0.9753   1.0000
   2.000   0.3346   0.02629   0.01552  -0.0445   0.9535   1.0000
   2.250   0.3903   0.02713   0.01627  -0.0506   0.9306   1.0000
   2.500   0.4399   0.02774   0.01686  -0.0551   0.9072   1.0000
   2.750   0.4966   0.02813   0.01730  -0.0604   0.8850   1.0000
   3.000   0.5444   0.02833   0.01756  -0.0638   0.8607   1.0000
   3.250   0.5920   0.02832   0.01767  -0.0667   0.8363   1.0000
   3.500   0.6493   0.02786   0.01741  -0.0706   0.8134   1.0000
   3.750   0.6996   0.02723   0.01695  -0.0727   0.7893   1.0000
   4.000   0.7402   0.02674   0.01662  -0.0731   0.7630   1.0000
   4.250   0.7797   0.02618   0.01627  -0.0730   0.7358   1.0000
   4.500   0.8162   0.02575   0.01596  -0.0723   0.7077   1.0000
   4.750   0.8496   0.02549   0.01580  -0.0713   0.6788   1.0000
   5.000   0.8796   0.02551   0.01594  -0.0699   0.6500   1.0000
   5.250   0.9069   0.02575   0.01623  -0.0684   0.6215   1.0000
   5.500   0.9320   0.02618   0.01672  -0.0668   0.5938   1.0000
   5.750   0.9555   0.02677   0.01739  -0.0651   0.5670   1.0000
   6.000   0.9782   0.02750   0.01824  -0.0634   0.5420   1.0000
   6.250   1.0029   0.02825   0.01914  -0.0620   0.5193   1.0000
   6.500   1.0240   0.02926   0.02035  -0.0604   0.4968   1.0000
   6.750   1.0450   0.03013   0.02141  -0.0586   0.4730   1.0000
   7.000   1.0655   0.03033   0.02170  -0.0560   0.4417   1.0000
   7.250   1.0787   0.02914   0.02026  -0.0514   0.3914   1.0000
   7.500   1.0832   0.02855   0.01952  -0.0463   0.3385   1.0000
   7.750   1.0798   0.02902   0.01996  -0.0408   0.2746   1.0000
   8.250   1.0682   0.03392   0.02346  -0.0306   0.1286   1.0000
   8.500   1.0867   0.03671   0.02607  -0.0287   0.1087   1.0000
   8.750   1.1096   0.03945   0.02882  -0.0275   0.0957   1.0000
   9.000   1.1328   0.04243   0.03201  -0.0265   0.0870   1.0000
   9.250   1.1580   0.04584   0.03559  -0.0258   0.0825   1.0000
   9.500   1.1799   0.05019   0.04023  -0.0250   0.0805   1.0000
   9.750   1.1892   0.05419   0.04479  -0.0228   0.0799   1.0000
  10.000   1.1925   0.05825   0.04935  -0.0204   0.0796   1.0000
  10.250   1.1898   0.06229   0.05386  -0.0178   0.0794   1.0000
  10.500   1.1809   0.06631   0.05829  -0.0151   0.0792   1.0000
  10.750   1.1692   0.07044   0.06273  -0.0126   0.0793   1.0000
  11.000   1.1532   0.07436   0.06690  -0.0101   0.0796   1.0000
  11.250   1.1382   0.07867   0.07137  -0.0084   0.0801   1.0000
  11.500   1.1205   0.08321   0.07607  -0.0075   0.0805   1.0000
  11.750   1.0369   0.09229   0.08553  -0.0132   0.0872   1.0000
  12.000   1.0054   0.10115   0.09443  -0.0189   0.0892   1.0000
  12.250   0.9849   0.10988   0.10314  -0.0240   0.0911   1.0000
  12.500   0.9780   0.11686   0.11011  -0.0266   0.0926   1.0000
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