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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 100,000
Max Cl/Cd: 67.3 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe484-il-100000.txt
Download as CSV file: xf-goe484-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3637   0.10331   0.09841  -0.0261   1.0000   0.0758
  -7.500  -0.3830   0.10369   0.09890  -0.0239   1.0000   0.0765
  -7.250  -0.3969   0.10385   0.09916  -0.0252   1.0000   0.0771
  -7.000  -0.4016   0.10344   0.09880  -0.0304   1.0000   0.0774
  -6.750  -0.3960   0.09657   0.09197  -0.0217   1.0000   0.0789
  -6.500  -0.3924   0.09352   0.08895  -0.0188   1.0000   0.0806
  -6.250  -0.3915   0.09119   0.08665  -0.0175   1.0000   0.0825
  -6.000  -0.3907   0.08893   0.08441  -0.0172   1.0000   0.0848
  -5.750  -0.3881   0.08666   0.08217  -0.0186   1.0000   0.0878
  -5.500  -0.3612   0.08504   0.08043  -0.0374   1.0000   0.0916
  -5.250  -0.3658   0.08066   0.07615  -0.0303   1.0000   0.0926
  -5.000  -0.3648   0.07773   0.07327  -0.0257   1.0000   0.0944
  -4.750  -0.3573   0.07522   0.07077  -0.0247   1.0000   0.0978
  -4.250  -0.3134   0.06833   0.06375  -0.0366   1.0000   0.1079
  -4.000  -0.3054   0.06574   0.06119  -0.0348   1.0000   0.1104
  -3.750  -0.2759   0.06298   0.05829  -0.0408   1.0000   0.1188
  -3.500  -0.2498   0.05910   0.05432  -0.0457   1.0000   0.1229
  -3.250  -0.2021   0.05722   0.05203  -0.0557   1.0000   0.1358
  -3.000  -0.1969   0.05342   0.04843  -0.0528   1.0000   0.1375
  -2.750  -0.1797   0.05119   0.04625  -0.0523   0.9987   0.1433
  -2.500  -0.1084   0.04832   0.04286  -0.0661   0.9928   0.1658
  -2.250  -0.0801   0.04488   0.03957  -0.0675   0.9869   0.1702
  -2.000  -0.0345   0.04232   0.03685  -0.0734   0.9810   0.1857
  -1.750   0.0139   0.04012   0.03439  -0.0798   0.9743   0.2113
  -1.500   0.0514   0.03797   0.03224  -0.0829   0.9677   0.2301
  -1.250   0.1350   0.03233   0.02493  -0.0932   0.9644   0.1214
  -1.000   0.1810   0.02941   0.02157  -0.0967   0.9597   0.1028
  -0.750   0.2219   0.02761   0.01935  -0.0992   0.9531   0.0968
  -0.500   0.2644   0.02622   0.01746  -0.1017   0.9464   0.0937
  -0.250   0.3032   0.02537   0.01645  -0.1038   0.9387   0.0946
   0.000   0.3436   0.02487   0.01590  -0.1062   0.9311   0.1008
   0.250   0.3785   0.02441   0.01533  -0.1075   0.9220   0.1054
   0.500   0.4205   0.02377   0.01483  -0.1101   0.9158   0.1137
   0.750   0.4524   0.02342   0.01457  -0.1108   0.9055   0.1289
   1.000   0.5009   0.02157   0.01424  -0.1150   0.9019   0.5707
   1.250   0.5352   0.02106   0.01412  -0.1160   0.8922   1.0000
   1.500   0.5788   0.02114   0.01403  -0.1188   0.8861   1.0000
   1.750   0.6076   0.02140   0.01420  -0.1191   0.8749   1.0000
   2.000   0.6539   0.02135   0.01408  -0.1223   0.8705   1.0000
   2.250   0.6791   0.02166   0.01438  -0.1219   0.8588   1.0000
   2.500   0.7113   0.02178   0.01450  -0.1225   0.8489   1.0000
   2.750   0.7639   0.02104   0.01380  -0.1260   0.8425   1.0000
   3.000   0.8020   0.02052   0.01334  -0.1268   0.8302   1.0000
   3.250   0.8504   0.01908   0.01197  -0.1281   0.8158   1.0000
   3.500   0.9012   0.01720   0.01013  -0.1291   0.7968   1.0000
   3.750   0.9296   0.01666   0.00968  -0.1277   0.7755   1.0000
   4.000   0.9624   0.01590   0.00895  -0.1267   0.7508   1.0000
   4.250   0.9848   0.01549   0.00857  -0.1241   0.7147   1.0000
   4.500   1.0108   0.01511   0.00810  -0.1219   0.6653   1.0000
   4.750   1.0304   0.01531   0.00785  -0.1184   0.5771   1.0000
   5.000   1.0294   0.01682   0.00808  -0.1120   0.3507   1.0000
   5.250   1.0258   0.01984   0.00950  -0.1071   0.1391   1.0000
   5.500   1.0388   0.02129   0.01068  -0.1045   0.1165   1.0000
   5.750   1.0547   0.02237   0.01179  -0.1022   0.1075   1.0000
   6.000   1.0679   0.02372   0.01311  -0.0996   0.1013   1.0000
   6.250   1.0854   0.02482   0.01426  -0.0977   0.0952   1.0000
   6.500   1.1039   0.02630   0.01564  -0.0960   0.0908   1.0000
   6.750   1.1309   0.02822   0.01745  -0.0957   0.0876   1.0000
   7.000   1.1583   0.02963   0.01897  -0.0953   0.0835   1.0000
   7.250   1.1881   0.03144   0.02084  -0.0954   0.0797   1.0000
   7.500   1.2215   0.03389   0.02330  -0.0961   0.0773   1.0000
   7.750   1.2519   0.03705   0.02660  -0.0964   0.0743   1.0000
   8.000   1.2755   0.03928   0.02922  -0.0952   0.0731   1.0000
   8.250   1.2984   0.04224   0.03259  -0.0939   0.0730   1.0000
   8.500   1.3166   0.04510   0.03589  -0.0920   0.0723   1.0000
   8.750   1.3313   0.04816   0.03940  -0.0897   0.0716   1.0000
   9.000   1.3463   0.05262   0.04423  -0.0878   0.0734   1.0000
   9.250   1.3510   0.05688   0.04944  -0.0831   0.0825   1.0000
  11.750   1.0876   0.13785   0.13328  -0.0871   0.1854   1.0000
  12.000   1.0395   0.14522   0.14051  -0.0964   0.1755   1.0000
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