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GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 626 AIRFOIL (goe626-il)
Reynolds number: 50,000
Max Cl/Cd: 30.55 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe626-il-50000-n5.txt
Download as CSV file: xf-goe626-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 626 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3385   0.11011   0.10227  -0.0483   1.0000   0.0913
 -10.750  -0.3562   0.10452   0.09675  -0.0494   1.0000   0.0924
 -10.500  -0.3749   0.09913   0.09145  -0.0502   1.0000   0.0938
 -10.250  -0.3720   0.09810   0.09048  -0.0485   1.0000   0.0955
 -10.000  -0.3754   0.09613   0.08859  -0.0473   1.0000   0.0978
  -9.750  -0.3948   0.09171   0.08426  -0.0473   1.0000   0.1004
  -9.500  -0.4768   0.07856   0.07124  -0.0509   1.0000   0.1038
  -9.250  -0.4507   0.08168   0.07445  -0.0470   1.0000   0.1063
  -9.000  -0.4567   0.08051   0.07338  -0.0449   1.0000   0.1093
  -8.750  -0.5108   0.07397   0.06697  -0.0443   1.0000   0.1122
  -8.500  -0.5841   0.06497   0.05803  -0.0455   1.0000   0.1136
  -8.250  -0.5649   0.06537   0.05855  -0.0449   0.9973   0.1190
  -8.000  -0.5538   0.06003   0.05316  -0.0528   0.9875   0.1292
  -7.750  -0.5315   0.05632   0.04936  -0.0596   0.9785   0.1407
  -7.250  -0.4524   0.06044   0.05342  -0.0597   0.9633   0.1581
  -6.750  -0.3909   0.05967   0.05248  -0.0657   0.9443   0.1843
  -6.500  -0.3571   0.05884   0.05152  -0.0696   0.9360   0.1980
  -6.250  -0.3342   0.05610   0.04861  -0.0745   0.9245   0.2109
  -6.000  -0.3096   0.05293   0.04522  -0.0799   0.9138   0.2243
  -5.750  -0.2740   0.05408   0.04634  -0.0789   0.9057   0.2284
  -5.500  -0.2507   0.05047   0.04246  -0.0843   0.8939   0.2408
  -5.000  -0.1902   0.04805   0.03973  -0.0886   0.8739   0.2579
  -4.750  -0.1490   0.04558   0.03692  -0.0946   0.8671   0.2717
  -4.500  -0.1283   0.04591   0.03730  -0.0922   0.8540   0.2756
  -4.250  -0.0852   0.04395   0.03502  -0.0975   0.8479   0.2894
  -4.000  -0.0663   0.04407   0.03518  -0.0952   0.8343   0.2936
  -3.750  -0.0209   0.04203   0.03278  -0.1008   0.8287   0.3070
  -3.500  -0.0032   0.04194   0.03274  -0.0985   0.8150   0.3107
  -3.250   0.0324   0.04110   0.03179  -0.1000   0.8073   0.3179
  -3.000   0.0628   0.03955   0.02992  -0.1027   0.7958   0.3264
  -2.750   0.0932   0.03906   0.02943  -0.1027   0.7868   0.3307
  -2.500   0.1234   0.03828   0.02854  -0.1035   0.7765   0.3365
  -2.250   0.1577   0.03702   0.02694  -0.1063   0.7665   0.3438
  -2.000   0.1894   0.03634   0.02623  -0.1068   0.7572   0.3478
  -1.750   0.2156   0.03588   0.02572  -0.1066   0.7463   0.3518
  -1.500   0.2520   0.03501   0.02469  -0.1082   0.7379   0.3568
  -1.250   0.2804   0.03438   0.02383  -0.1091   0.7263   0.3621
  -1.000   0.3182   0.03357   0.02290  -0.1107   0.7187   0.3665
  -0.750   0.3420   0.03331   0.02260  -0.1101   0.7069   0.3695
  -0.500   0.3814   0.03256   0.02172  -0.1118   0.6997   0.3737
  -0.250   0.4059   0.03234   0.02139  -0.1116   0.6876   0.3781
   0.000   0.4482   0.03158   0.02035  -0.1141   0.6807   0.3834
   0.250   0.4705   0.03152   0.02030  -0.1132   0.6688   0.3860
   0.500   0.5077   0.03102   0.01969  -0.1144   0.6612   0.3894
   0.750   0.5317   0.03103   0.01967  -0.1139   0.6500   0.3932
   1.000   0.5705   0.03061   0.01907  -0.1155   0.6428   0.3983
   1.250   0.5933   0.03077   0.01913  -0.1151   0.6315   0.4024
   1.500   0.6304   0.03044   0.01872  -0.1162   0.6244   0.4059
   1.750   0.6498   0.03075   0.01906  -0.1151   0.6136   0.4087
   2.000   0.6843   0.03062   0.01884  -0.1159   0.6062   0.4132
   2.250   0.7069   0.03097   0.01915  -0.1153   0.5965   0.4178
   2.500   0.7376   0.03107   0.01914  -0.1158   0.5884   0.4228
   2.750   0.7649   0.03127   0.01935  -0.1156   0.5807   0.4270
   3.000   0.7867   0.03169   0.01980  -0.1148   0.5718   0.4313
   3.250   0.8221   0.03168   0.01968  -0.1158   0.5655   0.4366
   3.500   0.8374   0.03240   0.02043  -0.1142   0.5562   0.4409
   3.750   0.8649   0.03263   0.02071  -0.1141   0.5492   0.4462
   4.000   0.8928   0.03293   0.02101  -0.1141   0.5429   0.4529
   4.250   0.9075   0.03372   0.02188  -0.1124   0.5344   0.4592
   4.500   0.9382   0.03385   0.02205  -0.1127   0.5283   0.4663
   4.750   0.9552   0.03457   0.02285  -0.1113   0.5209   0.4731
   5.000   0.9743   0.03518   0.02353  -0.1101   0.5133   0.4805
   5.250   1.0104   0.03501   0.02338  -0.1109   0.5076   0.4910
   5.500   1.0134   0.03622   0.02477  -0.1078   0.4981   0.4992
   5.750   1.0451   0.03605   0.02464  -0.1079   0.4908   0.5143
   6.000   1.0539   0.03689   0.02568  -0.1054   0.4816   0.5270
   6.250   1.0813   0.03674   0.02565  -0.1049   0.4732   0.5492
   6.500   1.0920   0.03735   0.02647  -0.1025   0.4639   0.5742
   7.000   1.1235   0.03724   0.02712  -0.0981   0.4484   1.0000
   7.250   1.1308   0.03835   0.02822  -0.0956   0.4403   1.0000
   7.500   1.1690   0.03826   0.02796  -0.0965   0.4345   1.0000
   7.750   1.1553   0.04033   0.03016  -0.0918   0.4261   1.0000
   8.000   1.1772   0.04083   0.03062  -0.0909   0.4192   1.0000
   8.250   1.1909   0.04173   0.03152  -0.0892   0.4122   1.0000
   8.500   1.1855   0.04364   0.03352  -0.0859   0.4038   1.0000
   8.750   1.2284   0.04294   0.03272  -0.0867   0.3977   1.0000
   9.000   1.1936   0.04669   0.03667  -0.0815   0.3881   1.0000
   9.250   1.2238   0.04655   0.03649  -0.0810   0.3814   1.0000
   9.500   1.2009   0.05009   0.04017  -0.0777   0.3722   1.0000
   9.750   1.2129   0.05125   0.04136  -0.0763   0.3647   1.0000
  10.000   1.2144   0.05333   0.04350  -0.0747   0.3570   1.0000
  10.250   1.1973   0.05713   0.04742  -0.0729   0.3472   1.0000
  10.500   1.2528   0.05441   0.04460  -0.0726   0.3425   1.0000
  10.750   1.1820   0.06380   0.05425  -0.0708   0.3288   1.0000
  11.000   1.2159   0.06263   0.05304  -0.0696   0.3233   1.0000
  11.250   1.1693   0.07092   0.06149  -0.0698   0.3104   1.0000
  11.750   1.1551   0.07897   0.06965  -0.0699   0.2924   1.0000
  12.250   1.1354   0.08862   0.07942  -0.0712   0.2752   1.0000
  12.750   1.1264   0.09672   0.08762  -0.0724   0.2586   1.0000
  13.000   1.0782   0.10915   0.10015  -0.0770   0.2458   1.0000
  13.250   1.1283   0.10290   0.09389  -0.0732   0.2425   1.0000
  13.750   1.1367   0.10784   0.09890  -0.0737   0.2268   1.0000
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