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GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il)
Reynolds number: 50,000
Max Cl/Cd: 28.86 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe322-il-50000-n5.txt
Download as CSV file: xf-goe322-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.1) 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  -0.2293   0.13357   0.12722  -0.0330   1.0000   0.0933
 -10.750  -0.2321   0.13248   0.12623  -0.0360   1.0000   0.0953
 -10.500  -0.2394   0.13200   0.12588  -0.0391   1.0000   0.0960
 -10.250  -0.2202   0.12604   0.11997  -0.0381   1.0000   0.0980
 -10.000  -0.2105   0.12290   0.11690  -0.0383   0.9939   0.1006
  -9.750  -0.1945   0.11930   0.11328  -0.0421   0.9731   0.1039
  -9.500  -0.1829   0.11625   0.11021  -0.0468   0.9556   0.1074
  -9.250  -0.1806   0.11451   0.10847  -0.0532   0.9377   0.1095
  -8.750  -0.1452   0.10566   0.09956  -0.0568   0.9145   0.1134
  -8.500  -0.1315   0.10251   0.09636  -0.0584   0.9029   0.1180
  -8.250  -0.1312   0.10071   0.09454  -0.0624   0.8901   0.1230
  -8.000  -0.1408   0.09978   0.09360  -0.0687   0.8768   0.1243
  -7.750  -0.1151   0.09440   0.08820  -0.0651   0.8698   0.1272
  -7.500  -0.1036   0.09144   0.08520  -0.0655   0.8616   0.1304
  -7.250  -0.0989   0.08912   0.08287  -0.0673   0.8517   0.1343
  -7.000  -0.1025   0.08779   0.08144  -0.0767   0.8416   0.1389
  -6.750  -0.0891   0.08389   0.07757  -0.0755   0.8342   0.1405
  -6.500  -0.0745   0.08072   0.07436  -0.0744   0.8281   0.1435
  -6.250  -0.0639   0.07825   0.07186  -0.0759   0.8196   0.1483
  -6.000  -0.0547   0.07564   0.06911  -0.0817   0.8126   0.1555
  -5.750  -0.0412   0.07293   0.06643  -0.0799   0.8051   0.1602
  -5.500  -0.0281   0.07067   0.06400  -0.0853   0.7980   0.1709
  -5.250   0.0025   0.06449   0.05728  -0.0929   0.7914   0.1095
  -4.750   0.0468   0.05625   0.04844  -0.0972   0.7795   0.0824
  -4.500   0.0648   0.05403   0.04615  -0.0977   0.7719   0.0809
  -4.250   0.0872   0.05155   0.04345  -0.0986   0.7658   0.0796
  -4.000   0.1115   0.04919   0.04078  -0.0997   0.7604   0.0796
  -3.750   0.1337   0.04727   0.03858  -0.1004   0.7529   0.0800
  -3.500   0.1598   0.04519   0.03617  -0.1010   0.7476   0.0800
  -3.250   0.1840   0.04345   0.03412  -0.1014   0.7412   0.0793
  -3.000   0.2087   0.04185   0.03220  -0.1016   0.7344   0.0788
  -2.750   0.2371   0.04015   0.03011  -0.1018   0.7296   0.0785
  -2.250   0.2874   0.03788   0.02721  -0.1016   0.7159   0.0795
  -2.000   0.3172   0.03671   0.02560  -0.1014   0.7113   0.0819
  -1.750   0.3390   0.03622   0.02491  -0.1010   0.7025   0.0839
  -1.500   0.3671   0.03532   0.02385  -0.1007   0.6970   0.0860
  -1.250   0.3907   0.03490   0.02330  -0.1002   0.6890   0.0878
  -1.000   0.4175   0.03426   0.02247  -0.0996   0.6821   0.0902
  -0.750   0.4446   0.03373   0.02171  -0.0989   0.6755   0.0935
  -0.500   0.4690   0.03348   0.02137  -0.0982   0.6671   0.0986
  -0.250   0.4993   0.03286   0.02060  -0.0978   0.6623   0.1075
   0.000   0.5184   0.03304   0.02080  -0.0969   0.6522   0.1150
   0.250   0.5474   0.03244   0.02011  -0.0964   0.6470   0.1298
   0.500   0.5670   0.03261   0.02032  -0.0956   0.6376   0.1551
   0.750   0.5945   0.03173   0.01987  -0.0955   0.6320   0.2361
   1.000   0.6188   0.03012   0.02002  -0.0947   0.6238   1.0000
   1.250   0.6445   0.03033   0.01988  -0.0940   0.6170   1.0000
   1.500   0.6666   0.03081   0.02013  -0.0932   0.6090   1.0000
   1.750   0.6905   0.03114   0.02024  -0.0925   0.6016   1.0000
   2.000   0.7146   0.03146   0.02038  -0.0918   0.5946   1.0000
   2.250   0.7363   0.03193   0.02072  -0.0910   0.5862   1.0000
   2.500   0.7637   0.03197   0.02057  -0.0905   0.5803   1.0000
   2.750   0.7816   0.03274   0.02128  -0.0895   0.5706   1.0000
   3.000   0.8132   0.03243   0.02079  -0.0892   0.5661   1.0000
   3.250   0.8266   0.03353   0.02187  -0.0879   0.5549   1.0000
   3.500   0.8586   0.03319   0.02138  -0.0876   0.5503   1.0000
   3.750   0.8707   0.03439   0.02258  -0.0863   0.5391   1.0000
   4.000   0.9031   0.03400   0.02205  -0.0861   0.5343   1.0000
   4.250   0.9142   0.03525   0.02334  -0.0846   0.5230   1.0000
   4.500   0.9470   0.03483   0.02280  -0.0844   0.5182   1.0000
   4.750   0.9563   0.03622   0.02423  -0.0828   0.5068   1.0000
   5.000   0.9902   0.03568   0.02359  -0.0827   0.5019   1.0000
   5.250   0.9974   0.03717   0.02513  -0.0809   0.4902   1.0000
   5.500   1.0293   0.03669   0.02455  -0.0806   0.4841   1.0000
   5.750   1.0395   0.03780   0.02570  -0.0789   0.4727   1.0000
   6.000   1.0537   0.03859   0.02650  -0.0774   0.4626   1.0000
   6.250   1.0821   0.03823   0.02608  -0.0768   0.4549   1.0000
   6.500   1.0870   0.03971   0.02761  -0.0747   0.4437   1.0000
   6.750   1.1222   0.03888   0.02670  -0.0746   0.4375   1.0000
   7.000   1.1172   0.04103   0.02895  -0.0719   0.4262   1.0000
   7.250   1.1375   0.04137   0.02926  -0.0708   0.4189   1.0000
   7.500   1.1432   0.04284   0.03079  -0.0690   0.4098   1.0000
   7.750   1.1550   0.04395   0.03194  -0.0677   0.4019   1.0000
   8.000   1.1669   0.04508   0.03310  -0.0665   0.3938   1.0000
   8.250   1.1755   0.04660   0.03466  -0.0653   0.3859   1.0000
   8.500   1.1873   0.04783   0.03593  -0.0642   0.3782   1.0000
   8.750   1.1972   0.04930   0.03744  -0.0632   0.3707   1.0000
   9.000   1.2043   0.05105   0.03927  -0.0622   0.3627   1.0000
   9.250   1.2244   0.05153   0.03975  -0.0613   0.3565   1.0000
   9.500   1.2154   0.05510   0.04344  -0.0603   0.3474   1.0000
   9.750   1.2534   0.05368   0.04197  -0.0595   0.3433   1.0000
  10.000   1.2158   0.06065   0.04915  -0.0588   0.3324   1.0000
  10.250   1.2464   0.05996   0.04849  -0.0579   0.3286   1.0000
  10.500   1.1983   0.06893   0.05762  -0.0581   0.3174   1.0000
  10.750   1.2206   0.06915   0.05791  -0.0572   0.3135   1.0000
  11.000   1.2586   0.06744   0.05621  -0.0561   0.3111   1.0000
  11.250   1.1766   0.08179   0.07076  -0.0580   0.2974   1.0000
  11.500   1.2079   0.08058   0.06959  -0.0568   0.2954   1.0000
  12.000   1.1374   0.09871   0.08789  -0.0602   0.2782   1.0000
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