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GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 389 AIRFOIL (goe389-il)
Reynolds number: 50,000
Max Cl/Cd: 37.63 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe389-il-50000-n5.txt
Download as CSV file: xf-goe389-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 389 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3437   0.10610   0.09928  -0.0299   1.0000   0.1319
  -8.500  -0.3597   0.10495   0.09829  -0.0323   1.0000   0.1365
  -8.250  -0.3782   0.10364   0.09717  -0.0337   1.0000   0.1372
  -8.000  -0.3579   0.09829   0.09180  -0.0316   1.0000   0.1394
  -7.750  -0.3565   0.09532   0.08890  -0.0307   1.0000   0.1408
  -7.500  -0.3769   0.08702   0.08067  -0.0388   1.0000   0.0790
  -7.250  -0.3765   0.08394   0.07765  -0.0379   1.0000   0.0778
  -7.000  -0.3799   0.08071   0.07449  -0.0384   1.0000   0.0773
  -6.750  -0.3832   0.07738   0.07120  -0.0391   1.0000   0.0771
  -6.500  -0.3854   0.07392   0.06775  -0.0398   1.0000   0.0769
  -6.250  -0.3856   0.07034   0.06416  -0.0406   1.0000   0.0764
  -6.000  -0.3835   0.06660   0.06036  -0.0414   1.0000   0.0753
  -5.750  -0.3786   0.06250   0.05615  -0.0428   1.0000   0.0739
  -5.500  -0.3703   0.05810   0.05156  -0.0447   1.0000   0.0727
  -5.250  -0.3582   0.05374   0.04692  -0.0466   1.0000   0.0720
  -5.000  -0.3327   0.04963   0.04241  -0.0503   0.9966   0.0743
  -4.750  -0.2962   0.04498   0.03716  -0.0556   0.9905   0.0763
  -4.500  -0.2573   0.04087   0.03240  -0.0602   0.9841   0.0763
  -4.250  -0.2161   0.03746   0.02833  -0.0644   0.9764   0.0769
  -4.000  -0.1745   0.03468   0.02490  -0.0679   0.9672   0.0780
  -3.750  -0.1333   0.03257   0.02227  -0.0712   0.9576   0.0819
  -3.500  -0.0915   0.03096   0.02042  -0.0743   0.9486   0.0859
  -3.250  -0.0530   0.02944   0.01855  -0.0763   0.9390   0.0880
  -3.000  -0.0156   0.02818   0.01695  -0.0780   0.9302   0.0906
  -2.750   0.0252   0.02706   0.01551  -0.0802   0.9226   0.0941
  -2.500   0.0594   0.02614   0.01458  -0.0813   0.9130   0.0987
  -2.250   0.1026   0.02531   0.01353  -0.0839   0.9062   0.1085
  -2.000   0.1357   0.02465   0.01292  -0.0850   0.8954   0.1248
  -1.750   0.1712   0.02386   0.01220  -0.0863   0.8856   0.1534
  -1.500   0.2089   0.02270   0.01166  -0.0883   0.8769   0.2677
  -1.250   0.2321   0.02117   0.01155  -0.0873   0.8654   0.5674
  -1.000   0.2711   0.02014   0.01110  -0.0877   0.8539   1.0000
  -0.750   0.3029   0.02016   0.01076  -0.0881   0.8410   1.0000
  -0.500   0.3339   0.02017   0.01048  -0.0884   0.8277   1.0000
  -0.250   0.3642   0.02018   0.01022  -0.0884   0.8141   1.0000
   0.000   0.3942   0.02019   0.01000  -0.0884   0.8002   1.0000
   0.250   0.4238   0.02019   0.00979  -0.0883   0.7858   1.0000
   0.500   0.4533   0.02020   0.00961  -0.0881   0.7713   1.0000
   0.750   0.4825   0.02023   0.00946  -0.0879   0.7565   1.0000
   1.000   0.5112   0.02029   0.00936  -0.0875   0.7411   1.0000
   1.250   0.5393   0.02039   0.00931  -0.0871   0.7255   1.0000
   1.500   0.5668   0.02054   0.00933  -0.0867   0.7095   1.0000
   1.750   0.5936   0.02073   0.00940  -0.0862   0.6932   1.0000
   2.000   0.6199   0.02096   0.00953  -0.0856   0.6770   1.0000
   2.250   0.6458   0.02122   0.00971  -0.0851   0.6612   1.0000
   2.500   0.6715   0.02149   0.00991  -0.0845   0.6457   1.0000
   2.750   0.6972   0.02178   0.01013  -0.0840   0.6310   1.0000
   3.000   0.7228   0.02208   0.01040  -0.0835   0.6172   1.0000
   3.250   0.7487   0.02239   0.01066  -0.0830   0.6042   1.0000
   3.500   0.7750   0.02268   0.01090  -0.0825   0.5924   1.0000
   3.750   0.8011   0.02301   0.01122  -0.0821   0.5810   1.0000
   4.000   0.8262   0.02343   0.01165  -0.0816   0.5695   1.0000
   4.250   0.8519   0.02384   0.01206  -0.0812   0.5591   1.0000
   4.500   0.8793   0.02418   0.01239  -0.0810   0.5503   1.0000
   4.750   0.9034   0.02473   0.01302  -0.0805   0.5398   1.0000
   5.000   0.9290   0.02523   0.01357  -0.0801   0.5308   1.0000
   5.250   0.9551   0.02573   0.01411  -0.0798   0.5223   1.0000
   5.500   0.9790   0.02637   0.01489  -0.0793   0.5132   1.0000
   5.750   1.0063   0.02683   0.01538  -0.0790   0.5054   1.0000
   6.000   1.0282   0.02757   0.01629  -0.0783   0.4954   1.0000
   6.250   1.0524   0.02816   0.01701  -0.0777   0.4861   1.0000
   6.500   1.0773   0.02868   0.01761  -0.0771   0.4761   1.0000
   6.750   1.0979   0.02938   0.01848  -0.0761   0.4645   1.0000
   7.000   1.1196   0.02998   0.01923  -0.0751   0.4529   1.0000
   7.250   1.1425   0.03049   0.01984  -0.0742   0.4414   1.0000
   7.500   1.1651   0.03096   0.02046  -0.0732   0.4294   1.0000
   7.750   1.1831   0.03169   0.02143  -0.0718   0.4170   1.0000
   8.000   1.2021   0.03246   0.02244  -0.0705   0.4062   1.0000
   8.250   1.2210   0.03304   0.02321  -0.0691   0.3935   1.0000
   8.500   1.2345   0.03342   0.02374  -0.0668   0.3748   1.0000
   8.750   1.2468   0.03369   0.02415  -0.0643   0.3548   1.0000
   9.000   1.2572   0.03432   0.02496  -0.0619   0.3371   1.0000
   9.250   1.2655   0.03515   0.02604  -0.0594   0.3193   1.0000
   9.500   1.2708   0.03599   0.02702  -0.0566   0.2982   1.0000
   9.750   1.2707   0.03704   0.02815  -0.0533   0.2733   1.0000
  10.000   1.2696   0.03835   0.02949  -0.0502   0.2480   1.0000
  10.250   1.2692   0.04001   0.03118  -0.0477   0.2233   1.0000
  10.500   1.2662   0.04211   0.03326  -0.0455   0.1963   1.0000
  10.750   1.2577   0.04492   0.03591  -0.0436   0.1668   1.0000
  11.000   1.2449   0.04852   0.03929  -0.0424   0.1420   1.0000
  11.500   1.2180   0.05707   0.04772  -0.0417   0.1098   1.0000
  11.750   1.2083   0.06138   0.05217  -0.0419   0.0941   1.0000
  12.000   1.1992   0.06583   0.05678  -0.0424   0.0758   1.0000
  12.250   1.1863   0.07087   0.06180  -0.0432   0.0669   1.0000
  12.500   1.1733   0.07607   0.06696  -0.0443   0.0615   1.0000
  12.750   1.1627   0.08101   0.07194  -0.0452   0.0569   1.0000
  13.000   1.1532   0.08586   0.07685  -0.0462   0.0531   1.0000
  13.250   1.1438   0.09074   0.08174  -0.0472   0.0501   1.0000
  13.500   1.1359   0.09539   0.08637  -0.0481   0.0476   1.0000
  13.750   1.1329   0.09941   0.09057  -0.0487   0.0447   1.0000
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