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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 50,000
Max Cl/Cd: 27.38 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe623-il-50000.txt
Download as CSV file: xf-goe623-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3361   0.10670   0.09983  -0.0257   1.0000   0.2500
  -8.500  -0.3327   0.10343   0.09663  -0.0254   1.0000   0.2576
  -8.250  -0.3452   0.10229   0.09562  -0.0253   1.0000   0.2680
  -8.000  -0.3275   0.09795   0.09130  -0.0240   1.0000   0.2773
  -7.750  -0.3635   0.09853   0.09213  -0.0227   1.0000   0.2850
  -7.500  -0.3349   0.09344   0.08700  -0.0213   1.0000   0.2962
  -7.250  -0.3868   0.09502   0.08889  -0.0175   1.0000   0.3015
  -7.000  -0.3593   0.09029   0.08413  -0.0158   1.0000   0.3149
  -6.750  -0.3689   0.08823   0.08220  -0.0126   1.0000   0.3227
  -6.500  -0.3986   0.08805   0.08219  -0.0087   1.0000   0.3329
  -6.250  -0.3925   0.08519   0.07938  -0.0055   1.0000   0.3458
  -6.000  -0.4005   0.08329   0.07757  -0.0021   1.0000   0.3593
  -5.750  -0.4103   0.08155   0.07594   0.0014   1.0000   0.3749
  -5.500  -0.4188   0.07982   0.07429   0.0050   1.0000   0.3928
  -5.250  -0.4320   0.07840   0.07297   0.0086   1.0000   0.4130
  -4.750  -0.4200   0.05376   0.04677  -0.0349   1.0000   0.1747
  -4.500  -0.4034   0.05033   0.04315  -0.0353   1.0000   0.1680
  -4.250  -0.3770   0.04505   0.03688  -0.0387   1.0000   0.1567
  -4.000  -0.3550   0.04227   0.03368  -0.0395   1.0000   0.1564
  -3.750  -0.3334   0.04001   0.03112  -0.0400   1.0000   0.1595
  -3.500  -0.3125   0.03841   0.02934  -0.0401   1.0000   0.1635
  -3.250  -0.2888   0.03668   0.02721  -0.0405   1.0000   0.1668
  -3.000  -0.2637   0.03518   0.02516  -0.0409   1.0000   0.1723
  -2.750  -0.2425   0.03415   0.02413  -0.0409   1.0000   0.1824
  -2.500  -0.2192   0.03317   0.02294  -0.0410   1.0000   0.1955
  -2.250  -0.1956   0.03228   0.02195  -0.0410   1.0000   0.2145
  -2.000  -0.1486   0.03132   0.02107  -0.0449   0.9926   0.2718
  -1.750  -0.1048   0.03082   0.02091  -0.0485   0.9846   0.3598
  -1.500  -0.0645   0.03037   0.02080  -0.0514   0.9761   0.4448
  -1.250  -0.0236   0.02938   0.02086  -0.0536   0.9690   0.5984
  -1.000   0.0116   0.02866   0.02062  -0.0540   0.9587   1.0000
  -0.750   0.0462   0.02945   0.02091  -0.0565   0.9484   1.0000
  -0.500   0.0850   0.03036   0.02140  -0.0596   0.9391   1.0000
  -0.250   0.1204   0.03120   0.02194  -0.0621   0.9290   1.0000
   0.000   0.1489   0.03202   0.02252  -0.0634   0.9187   1.0000
   0.250   0.1875   0.03294   0.02319  -0.0663   0.9091   1.0000
   0.500   0.2165   0.03377   0.02384  -0.0675   0.8983   1.0000
   0.750   0.2433   0.03464   0.02456  -0.0684   0.8873   1.0000
   1.000   0.2800   0.03553   0.02528  -0.0707   0.8766   1.0000
   1.250   0.3123   0.03636   0.02599  -0.0723   0.8650   1.0000
   1.500   0.3355   0.03724   0.02678  -0.0724   0.8526   1.0000
   1.750   0.3642   0.03811   0.02756  -0.0733   0.8403   1.0000
   2.000   0.3988   0.03890   0.02828  -0.0749   0.8279   1.0000
   2.250   0.4398   0.03952   0.02884  -0.0771   0.8154   1.0000
   2.500   0.4631   0.04033   0.02962  -0.0769   0.8011   1.0000
   2.750   0.4895   0.04108   0.03034  -0.0770   0.7864   1.0000
   3.000   0.5184   0.04172   0.03097  -0.0772   0.7713   1.0000
   3.250   0.5493   0.04222   0.03148  -0.0775   0.7558   1.0000
   3.500   0.5819   0.04258   0.03184  -0.0778   0.7399   1.0000
   3.750   0.6164   0.04273   0.03203  -0.0780   0.7239   1.0000
   4.000   0.6527   0.04266   0.03200  -0.0782   0.7079   1.0000
   4.250   0.6910   0.04233   0.03174  -0.0783   0.6920   1.0000
   4.500   0.7285   0.04183   0.03130  -0.0779   0.6762   1.0000
   4.750   0.7653   0.04119   0.03072  -0.0773   0.6605   1.0000
   5.000   0.8020   0.04042   0.03003  -0.0764   0.6446   1.0000
   5.250   0.8390   0.03959   0.02926  -0.0755   0.6286   1.0000
   5.500   0.8775   0.03858   0.02834  -0.0747   0.6124   1.0000
   6.000   0.9246   0.03893   0.02881  -0.0712   0.5731   1.0000
   6.250   0.9563   0.03856   0.02850  -0.0701   0.5550   1.0000
   6.500   0.9881   0.03828   0.02827  -0.0691   0.5373   1.0000
   6.750   1.0185   0.03818   0.02820  -0.0681   0.5201   1.0000
   7.000   1.0462   0.03836   0.02842  -0.0671   0.5035   1.0000
   7.250   1.0690   0.03904   0.02916  -0.0658   0.4878   1.0000
   7.500   1.0855   0.04034   0.03057  -0.0644   0.4734   1.0000
   7.750   1.0982   0.04199   0.03234  -0.0628   0.4601   1.0000
   8.000   1.1112   0.04367   0.03416  -0.0613   0.4482   1.0000
   8.250   1.1446   0.04384   0.03436  -0.0610   0.4381   1.0000
   8.500   1.1399   0.04711   0.03784  -0.0587   0.4281   1.0000
   8.750   1.1355   0.05061   0.04150  -0.0567   0.4201   1.0000
   9.000   1.1296   0.05423   0.04526  -0.0548   0.4122   1.0000
   9.250   0.9451   0.07938   0.07011  -0.0565   0.4053   1.0000
   9.500   0.9003   0.08942   0.08010  -0.0590   0.4020   1.0000
   9.750   0.8843   0.09577   0.08646  -0.0604   0.3998   1.0000
  10.000   0.8624   0.10313   0.09384  -0.0626   0.4027   1.0000
  10.250   0.8591   0.10875   0.09952  -0.0642   0.4067   1.0000
  10.500   0.8693   0.11318   0.10406  -0.0653   0.4090   1.0000
  12.000   1.3937   0.05574   0.04813  -0.0366   0.2562   1.0000
  12.250   1.3544   0.06038   0.05309  -0.0319   0.2536   1.0000
  12.500   1.3089   0.06710   0.06004  -0.0293   0.2539   1.0000
  12.750   1.2563   0.07665   0.06970  -0.0295   0.2567   1.0000
  13.000   1.2442   0.07928   0.07241  -0.0279   0.2409   1.0000
  13.250   1.3253   0.06532   0.05764  -0.0196   0.1654   1.0000
  13.500   1.3146   0.06837   0.06065  -0.0181   0.1525   1.0000
  13.750   1.2855   0.07447   0.06706  -0.0181   0.1489   1.0000
  14.000   1.2806   0.07759   0.07012  -0.0174   0.1385   1.0000
  14.250   1.2481   0.08514   0.07796  -0.0190   0.1377   1.0000
  14.500   1.2095   0.09446   0.08751  -0.0222   0.1389   1.0000
  14.750   1.1685   0.10531   0.09847  -0.0267   0.1407   1.0000
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