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GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 100,000
Max Cl/Cd: 55.73 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe321-il-100000-n5.txt
Download as CSV file: xf-goe321-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2968   0.11175   0.10706  -0.0206   1.0000   0.0546
  -9.250  -0.2976   0.10946   0.10484  -0.0249   1.0000   0.0561
  -9.000  -0.3024   0.10737   0.10284  -0.0303   1.0000   0.0566
  -8.750  -0.2888   0.10275   0.09826  -0.0318   0.9663   0.0571
  -8.500  -0.2677   0.09846   0.09393  -0.0315   0.9350   0.0583
  -8.250  -0.2556   0.09518   0.09061  -0.0329   0.9000   0.0594
  -8.000  -0.2479   0.09224   0.08760  -0.0341   0.8714   0.0605
  -7.750  -0.2426   0.08940   0.08470  -0.0353   0.8494   0.0618
  -7.500  -0.2388   0.08661   0.08184  -0.0373   0.8319   0.0632
  -7.250  -0.1758   0.07189   0.06711  -0.0515   0.7858   0.0670
  -7.000  -0.1611   0.06865   0.06383  -0.0465   0.7774   0.0684
  -6.750  -0.1516   0.06546   0.06062  -0.0467   0.7685   0.0699
  -6.500  -0.1439   0.06208   0.05717  -0.0484   0.7616   0.0714
  -6.250  -0.1349   0.05844   0.05349  -0.0512   0.7535   0.0732
  -6.000  -0.1244   0.05464   0.04958  -0.0549   0.7468   0.0756
  -5.750  -0.1072   0.05040   0.04490  -0.0642   0.7396   0.0783
  -5.500  -0.0943   0.04595   0.04043  -0.0647   0.7329   0.0789
  -5.250  -0.0811   0.04258   0.03706  -0.0639   0.7271   0.0800
  -5.000  -0.0655   0.03985   0.03433  -0.0637   0.7193   0.0819
  -4.750  -0.0475   0.03715   0.03151  -0.0645   0.7131   0.0855
  -4.500  -0.0204   0.03386   0.02767  -0.0688   0.7064   0.0924
  -4.000   0.0206   0.03990   0.03245  -0.0734   0.7097   0.0564
  -3.750   0.0442   0.03770   0.03019  -0.0738   0.7026   0.0555
  -3.500   0.0698   0.03556   0.02782  -0.0742   0.6969   0.0547
  -3.250   0.0973   0.03354   0.02544  -0.0746   0.6911   0.0553
  -3.000   0.1250   0.03169   0.02328  -0.0749   0.6848   0.0556
  -2.750   0.1521   0.03002   0.02130  -0.0749   0.6796   0.0551
  -2.500   0.1799   0.02848   0.01950  -0.0751   0.6735   0.0547
  -2.250   0.2081   0.02710   0.01783  -0.0751   0.6677   0.0545
  -2.000   0.2363   0.02588   0.01630  -0.0750   0.6633   0.0545
  -1.750   0.2649   0.02485   0.01501  -0.0750   0.6580   0.0548
  -1.500   0.2936   0.02406   0.01391  -0.0749   0.6525   0.0564
  -1.250   0.3213   0.02321   0.01295  -0.0748   0.6479   0.0579
  -1.000   0.3494   0.02254   0.01219  -0.0748   0.6432   0.0588
  -0.750   0.3774   0.02194   0.01152  -0.0747   0.6377   0.0597
  -0.500   0.4052   0.02136   0.01084  -0.0745   0.6326   0.0608
  -0.250   0.4328   0.02084   0.01027  -0.0742   0.6261   0.0623
   0.000   0.4601   0.02040   0.00976  -0.0739   0.6188   0.0648
   0.250   0.4872   0.01995   0.00927  -0.0735   0.6128   0.0682
   0.500   0.5139   0.01962   0.00902  -0.0733   0.6059   0.0715
   0.750   0.5409   0.01930   0.00866  -0.0728   0.6006   0.0751
   1.000   0.5680   0.01907   0.00837  -0.0725   0.5944   0.0797
   1.250   0.5950   0.01887   0.00817  -0.0723   0.5871   0.0893
   1.500   0.6226   0.01864   0.00786  -0.0719   0.5806   0.1034
   1.750   0.6500   0.01833   0.00775  -0.0719   0.5721   0.1528
   2.000   0.6805   0.01633   0.00755  -0.0719   0.5647   1.0000
   2.250   0.7070   0.01648   0.00757  -0.0716   0.5557   1.0000
   2.500   0.7339   0.01658   0.00747  -0.0711   0.5481   1.0000
   2.750   0.7602   0.01674   0.00755  -0.0708   0.5385   1.0000
   3.000   0.7868   0.01687   0.00755  -0.0705   0.5303   1.0000
   3.250   0.8130   0.01705   0.00767  -0.0701   0.5208   1.0000
   3.500   0.8395   0.01722   0.00775  -0.0698   0.5128   1.0000
   3.750   0.8656   0.01742   0.00793  -0.0695   0.5034   1.0000
   4.000   0.8916   0.01762   0.00807  -0.0692   0.4942   1.0000
   4.250   0.9174   0.01780   0.00822  -0.0688   0.4841   1.0000
   4.500   0.9429   0.01803   0.00847  -0.0685   0.4727   1.0000
   4.750   0.9683   0.01823   0.00866  -0.0681   0.4614   1.0000
   5.000   0.9935   0.01844   0.00884  -0.0677   0.4491   1.0000
   5.250   1.0182   0.01868   0.00912  -0.0673   0.4346   1.0000
   5.500   1.0426   0.01893   0.00937  -0.0668   0.4186   1.0000
   5.750   1.0664   0.01922   0.00964  -0.0662   0.4001   1.0000
   6.000   1.0895   0.01955   0.00990  -0.0656   0.3806   1.0000
   6.250   1.1115   0.01996   0.01020  -0.0648   0.3616   1.0000
   6.500   1.1324   0.02049   0.01059  -0.0639   0.3436   1.0000
   6.750   1.1525   0.02110   0.01111  -0.0629   0.3271   1.0000
   7.000   1.1721   0.02178   0.01170  -0.0620   0.3122   1.0000
   7.250   1.1913   0.02247   0.01235  -0.0610   0.2989   1.0000
   7.500   1.2101   0.02320   0.01305  -0.0599   0.2873   1.0000
   7.750   1.2281   0.02396   0.01375  -0.0588   0.2775   1.0000
   8.000   1.2470   0.02466   0.01449  -0.0579   0.2686   1.0000
   8.250   1.2645   0.02544   0.01522  -0.0567   0.2618   1.0000
   8.500   1.2832   0.02616   0.01602  -0.0557   0.2553   1.0000
   8.750   1.3007   0.02693   0.01680  -0.0546   0.2498   1.0000
   9.000   1.3182   0.02773   0.01757  -0.0535   0.2455   1.0000
   9.250   1.3364   0.02849   0.01843  -0.0525   0.2411   1.0000
   9.500   1.3539   0.02928   0.01930  -0.0515   0.2372   1.0000
   9.750   1.3711   0.03009   0.02013  -0.0504   0.2340   1.0000
  10.000   1.3891   0.03090   0.02091  -0.0493   0.2314   1.0000
  10.250   1.4054   0.03176   0.02192  -0.0482   0.2284   1.0000
  10.500   1.4214   0.03266   0.02295  -0.0471   0.2253   1.0000
  10.750   1.4375   0.03357   0.02396  -0.0460   0.2225   1.0000
  11.000   1.4546   0.03448   0.02494  -0.0451   0.2201   1.0000
  11.250   1.4735   0.03538   0.02589  -0.0444   0.2181   1.0000
  11.500   1.4936   0.03630   0.02689  -0.0438   0.2163   1.0000
  11.750   1.5075   0.03745   0.02824  -0.0427   0.2143   1.0000
  12.000   1.5189   0.03867   0.02966  -0.0415   0.2117   1.0000
  12.250   1.5292   0.03991   0.03105  -0.0403   0.2085   1.0000
  12.500   1.5395   0.04105   0.03227  -0.0392   0.2047   1.0000
  12.750   1.5464   0.04245   0.03374  -0.0380   0.2005   1.0000
  13.000   1.5446   0.04443   0.03597  -0.0367   0.1961   1.0000
  13.250   1.5470   0.04616   0.03780  -0.0357   0.1913   1.0000
  13.500   1.5534   0.04768   0.03932  -0.0349   0.1867   1.0000
  13.750   1.5468   0.05045   0.04238  -0.0343   0.1825   1.0000
  14.000   1.5439   0.05294   0.04504  -0.0338   0.1777   1.0000
  14.250   1.5480   0.05471   0.04673  -0.0333   0.1723   1.0000
  14.500   1.5357   0.05848   0.05083  -0.0334   0.1681   1.0000
  14.750   1.5268   0.06196   0.05449  -0.0336   0.1630   1.0000
  15.000   1.5240   0.06466   0.05720  -0.0336   0.1576   1.0000
  15.250   1.5107   0.06912   0.06194  -0.0344   0.1535   1.0000
  15.500   1.4985   0.07365   0.06671  -0.0354   0.1490   1.0000
  15.750   1.4902   0.07774   0.07092  -0.0364   0.1445   1.0000
  16.000   1.4783   0.08261   0.07599  -0.0378   0.1403   1.0000
  16.250   1.4592   0.08891   0.08258  -0.0398   0.1361   1.0000
  16.500   1.4411   0.09521   0.08907  -0.0421   0.1317   1.0000
  16.750   1.4211   0.10202   0.09606  -0.0447   0.1277   1.0000
  17.000   1.3863   0.11180   0.10611  -0.0487   0.1255   1.0000
  17.250   1.3383   0.12462   0.11915  -0.0545   0.1247   1.0000
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