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GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 526 AIRFOIL (goe526-il)
Reynolds number: 50,000
Max Cl/Cd: 33.26 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe526-il-50000-n5.txt
Download as CSV file: xf-goe526-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 526 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3204   0.10460   0.09718  -0.0409   1.0000   0.0986
  -9.000  -0.3273   0.10211   0.09479  -0.0399   1.0000   0.0968
  -8.500  -0.3931   0.09640   0.08938  -0.0394   1.0000   0.0906
  -8.250  -0.4074   0.09471   0.08778  -0.0368   1.0000   0.0904
  -8.000  -0.4235   0.09308   0.08626  -0.0341   1.0000   0.0900
  -7.750  -0.4381   0.09108   0.08432  -0.0320   1.0000   0.0897
  -7.500  -0.4304   0.08660   0.07980  -0.0362   0.9934   0.0893
  -7.250  -0.4189   0.08173   0.07487  -0.0410   0.9849   0.0887
  -7.000  -0.4086   0.07683   0.06986  -0.0456   0.9763   0.0880
  -6.750  -0.3973   0.07166   0.06455  -0.0503   0.9684   0.0876
  -6.500  -0.3891   0.06658   0.05926  -0.0540   0.9595   0.0881
  -6.250  -0.3805   0.06133   0.05370  -0.0572   0.9512   0.0893
  -6.000  -0.3693   0.05615   0.04807  -0.0598   0.9435   0.0901
  -5.750  -0.3575   0.05166   0.04308  -0.0609   0.9362   0.0906
  -5.500  -0.3383   0.04949   0.04079  -0.0612   0.9296   0.0916
  -5.250  -0.3117   0.04762   0.03877  -0.0626   0.9248   0.0935
  -5.000  -0.2966   0.04588   0.03682  -0.0617   0.9171   0.0960
  -4.750  -0.2743   0.04340   0.03392  -0.0623   0.9112   0.0990
  -4.500  -0.2476   0.04057   0.03046  -0.0633   0.9066   0.1017
  -4.250  -0.2316   0.03916   0.02881  -0.0619   0.8987   0.1040
  -4.000  -0.2032   0.03825   0.02782  -0.0626   0.8934   0.1079
  -3.750  -0.1754   0.03691   0.02614  -0.0630   0.8882   0.1127
  -3.500  -0.1544   0.03564   0.02449  -0.0621   0.8806   0.1169
  -3.250  -0.1225   0.03494   0.02378  -0.0631   0.8755   0.1225
  -3.000  -0.0971   0.03408   0.02263  -0.0627   0.8686   0.1288
  -2.750  -0.0688   0.03336   0.02182  -0.0629   0.8612   0.1354
  -2.500  -0.0279   0.03247   0.02065  -0.0650   0.8562   0.1460
  -2.250  -0.0077   0.03201   0.02024  -0.0637   0.8457   0.1533
  -2.000   0.0345   0.03119   0.01928  -0.0659   0.8401   0.1667
  -1.750   0.0600   0.03084   0.01885  -0.0653   0.8304   0.1792
  -1.500   0.1007   0.03021   0.01819  -0.0673   0.8242   0.1961
  -1.250   0.1324   0.02978   0.01776  -0.0678   0.8165   0.2134
  -1.000   0.1635   0.02938   0.01738  -0.0682   0.8083   0.2335
  -0.750   0.2060   0.02868   0.01679  -0.0704   0.8035   0.2614
  -0.500   0.2229   0.02857   0.01679  -0.0685   0.7920   0.2845
  -0.250   0.2609   0.02780   0.01628  -0.0698   0.7865   0.3315
   0.000   0.2761   0.02740   0.01636  -0.0676   0.7752   0.4026
   0.250   0.4000   0.02560   0.01587  -0.0844   0.7730   1.0000
   0.500   0.4314   0.02556   0.01559  -0.0845   0.7651   1.0000
   0.750   0.4521   0.02572   0.01560  -0.0829   0.7538   1.0000
   1.000   0.4742   0.02588   0.01561  -0.0815   0.7432   1.0000
   1.250   0.5039   0.02583   0.01542  -0.0813   0.7343   1.0000
   1.500   0.5211   0.02611   0.01561  -0.0792   0.7220   1.0000
   1.750   0.5567   0.02588   0.01525  -0.0797   0.7146   1.0000
   2.000   0.5704   0.02626   0.01557  -0.0771   0.7011   1.0000
   2.250   0.5918   0.02644   0.01568  -0.0757   0.6897   1.0000
   2.500   0.6218   0.02636   0.01551  -0.0754   0.6805   1.0000
   2.750   0.6371   0.02673   0.01584  -0.0730   0.6673   1.0000
   3.000   0.6609   0.02686   0.01592  -0.0719   0.6566   1.0000
   3.250   0.6868   0.02691   0.01592  -0.0710   0.6463   1.0000
   3.500   0.7026   0.02732   0.01632  -0.0689   0.6335   1.0000
   3.750   0.7288   0.02741   0.01636  -0.0681   0.6238   1.0000
   4.000   0.7505   0.02764   0.01657  -0.0667   0.6128   1.0000
   4.250   0.7673   0.02809   0.01703  -0.0648   0.6009   1.0000
   4.500   0.8005   0.02795   0.01684  -0.0650   0.5931   1.0000
   4.750   0.8130   0.02858   0.01749  -0.0625   0.5805   1.0000
   5.000   0.8332   0.02892   0.01784  -0.0610   0.5697   1.0000
   5.250   0.8636   0.02879   0.01768  -0.0607   0.5600   1.0000
   5.500   0.8777   0.02929   0.01820  -0.0584   0.5470   1.0000
   5.750   0.8972   0.02955   0.01846  -0.0566   0.5345   1.0000
   6.000   0.9217   0.02953   0.01840  -0.0554   0.5221   1.0000
   6.250   0.9468   0.02952   0.01835  -0.0543   0.5095   1.0000
   6.500   0.9605   0.03005   0.01892  -0.0520   0.4963   1.0000
   6.750   0.9789   0.03047   0.01936  -0.0503   0.4847   1.0000
   7.000   1.0075   0.03055   0.01940  -0.0498   0.4745   1.0000
   7.250   1.0193   0.03128   0.02023  -0.0475   0.4627   1.0000
   7.500   1.0373   0.03180   0.02078  -0.0458   0.4514   1.0000
   7.750   1.0639   0.03199   0.02094  -0.0451   0.4402   1.0000
   8.000   1.0735   0.03281   0.02187  -0.0425   0.4280   1.0000
   8.250   1.0874   0.03347   0.02260  -0.0404   0.4160   1.0000
   8.500   1.1071   0.03390   0.02303  -0.0389   0.4036   1.0000
   8.750   1.1201   0.03449   0.02365  -0.0366   0.3900   1.0000
   9.000   1.1226   0.03545   0.02469  -0.0331   0.3760   1.0000
   9.250   1.1276   0.03633   0.02562  -0.0301   0.3613   1.0000
   9.500   1.1322   0.03723   0.02654  -0.0272   0.3461   1.0000
   9.750   1.1366   0.03820   0.02753  -0.0244   0.3310   1.0000
  10.000   1.1411   0.03924   0.02858  -0.0218   0.3161   1.0000
  10.250   1.1465   0.04032   0.02966  -0.0195   0.3019   1.0000
  10.500   1.1489   0.04172   0.03112  -0.0173   0.2878   1.0000
  10.750   1.1501   0.04333   0.03280  -0.0152   0.2741   1.0000
  11.000   1.1523   0.04497   0.03448  -0.0133   0.2610   1.0000
  11.250   1.1552   0.04664   0.03616  -0.0116   0.2486   1.0000
  11.500   1.1591   0.04826   0.03777  -0.0101   0.2371   1.0000
  11.750   1.1634   0.04991   0.03938  -0.0087   0.2262   1.0000
  12.000   1.1634   0.05216   0.04171  -0.0075   0.2153   1.0000
  12.250   1.1664   0.05418   0.04374  -0.0063   0.2058   1.0000
  12.500   1.1725   0.05583   0.04530  -0.0052   0.1967   1.0000
  12.750   1.1712   0.05854   0.04813  -0.0044   0.1878   1.0000
  13.000   1.1788   0.06025   0.04975  -0.0034   0.1798   1.0000
  13.250   1.1775   0.06314   0.05279  -0.0029   0.1723   1.0000
  13.500   1.1880   0.06467   0.05423  -0.0020   0.1649   1.0000
  13.750   1.1811   0.06837   0.05817  -0.0018   0.1587   1.0000
  14.000   1.1901   0.07020   0.05998  -0.0011   0.1524   1.0000
  14.250   1.1875   0.07356   0.06348  -0.0010   0.1473   1.0000
  14.500   1.1769   0.07800   0.06816  -0.0016   0.1426   1.0000
  14.750   1.1826   0.08030   0.07049  -0.0013   0.1376   1.0000
  15.000   1.1802   0.08390   0.07421  -0.0016   0.1337   1.0000
  15.250   1.1529   0.09127   0.08190  -0.0040   0.1309   1.0000
  15.500   1.1239   0.09951   0.09039  -0.0071   0.1281   1.0000
  15.750   1.1100   0.10548   0.09649  -0.0093   0.1247   1.0000
  16.000   1.1256   0.10619   0.09717  -0.0086   0.1211   1.0000
  16.250   0.9717   0.14391   0.13518  -0.0297   0.1179   1.0000
  16.500   0.9496   0.15435   0.14561  -0.0351   0.1138   1.0000
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