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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 50,000
Max Cl/Cd: 34.43 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe316-il-50000-n5.txt
Download as CSV file: xf-goe316-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3692   0.10063   0.09422  -0.0127   1.0000   0.0941
  -7.750  -0.3693   0.09813   0.09182  -0.0160   1.0000   0.0978
  -7.500  -0.3696   0.09631   0.09005  -0.0256   1.0000   0.1000
  -7.250  -0.3567   0.09100   0.08483  -0.0207   1.0000   0.1036
  -7.000  -0.3478   0.08779   0.08167  -0.0219   1.0000   0.1099
  -6.750  -0.3433   0.08603   0.07986  -0.0334   1.0000   0.1150
  -6.500  -0.3323   0.08099   0.07497  -0.0274   1.0000   0.1191
  -6.250  -0.3231   0.07801   0.07202  -0.0294   1.0000   0.1259
  -6.000  -0.3159   0.07489   0.06892  -0.0332   1.0000   0.1313
  -5.750  -0.3090   0.07189   0.06600  -0.0313   1.0000   0.1363
  -5.500  -0.3054   0.06977   0.06382  -0.0344   1.0000   0.1457
  -5.250  -0.3042   0.06717   0.06137  -0.0308   1.0000   0.1513
  -5.000  -0.2965   0.06462   0.05881  -0.0318   0.9967   0.1644
  -4.750  -0.2646   0.06083   0.05490  -0.0376   0.9839   0.1932
  -4.500  -0.2357   0.05729   0.05132  -0.0409   0.9719   0.2251
  -4.250  -0.2077   0.05396   0.04800  -0.0425   0.9606   0.2619
  -3.750  -0.0786   0.04373   0.03605  -0.0634   0.9348   0.1090
  -3.500  -0.0359   0.04034   0.03213  -0.0667   0.9197   0.0921
  -3.250   0.0064   0.03786   0.02893  -0.0691   0.9031   0.0841
  -3.000   0.0413   0.03565   0.02634  -0.0705   0.8844   0.0837
  -2.750   0.0743   0.03398   0.02420  -0.0710   0.8649   0.0847
  -2.500   0.1050   0.03224   0.02213  -0.0711   0.8469   0.0840
  -2.250   0.1345   0.03072   0.02029  -0.0710   0.8305   0.0831
  -2.000   0.1633   0.02944   0.01869  -0.0706   0.8149   0.0824
  -1.750   0.1915   0.02835   0.01729  -0.0700   0.7994   0.0821
  -1.500   0.2192   0.02740   0.01606  -0.0693   0.7839   0.0823
  -1.250   0.2467   0.02672   0.01506  -0.0685   0.7681   0.0846
  -1.000   0.2734   0.02591   0.01407  -0.0677   0.7522   0.0870
  -0.750   0.2995   0.02517   0.01319  -0.0666   0.7360   0.0884
  -0.500   0.3265   0.02457   0.01241  -0.0656   0.7198   0.0895
  -0.250   0.3530   0.02405   0.01174  -0.0647   0.7033   0.0911
   0.000   0.3789   0.02361   0.01115  -0.0637   0.6866   0.0931
   0.250   0.4045   0.02325   0.01063  -0.0627   0.6697   0.0961
   0.500   0.4301   0.02297   0.01024  -0.0620   0.6515   0.1021
   0.750   0.4558   0.02269   0.00989  -0.0613   0.6336   0.1101
   1.000   0.4819   0.02248   0.00956  -0.0607   0.6162   0.1170
   1.250   0.5082   0.02230   0.00928  -0.0600   0.5991   0.1283
   1.500   0.5347   0.02190   0.00906  -0.0597   0.5828   0.1725
   1.750   0.5611   0.02007   0.00889  -0.0587   0.5673   1.0000
   2.000   0.5874   0.02037   0.00885  -0.0581   0.5525   1.0000
   2.250   0.6138   0.02071   0.00892  -0.0577   0.5389   1.0000
   2.500   0.6402   0.02108   0.00908  -0.0573   0.5270   1.0000
   2.750   0.6667   0.02145   0.00923  -0.0569   0.5166   1.0000
   3.000   0.6929   0.02191   0.00959  -0.0567   0.5052   1.0000
   3.250   0.7192   0.02238   0.00995  -0.0565   0.4957   1.0000
   3.500   0.7455   0.02283   0.01029  -0.0562   0.4873   1.0000
   3.750   0.7716   0.02337   0.01081  -0.0561   0.4790   1.0000
   4.000   0.7979   0.02388   0.01128  -0.0559   0.4724   1.0000
   4.250   0.8240   0.02449   0.01189  -0.0558   0.4660   1.0000
   4.500   0.8498   0.02509   0.01252  -0.0557   0.4597   1.0000
   4.750   0.8762   0.02561   0.01300  -0.0555   0.4547   1.0000
   5.000   0.9009   0.02639   0.01392  -0.0555   0.4481   1.0000
   5.250   0.9265   0.02703   0.01462  -0.0553   0.4431   1.0000
   5.500   0.9526   0.02767   0.01529  -0.0551   0.4392   1.0000
   5.750   0.9762   0.02864   0.01647  -0.0551   0.4339   1.0000
   6.000   1.0008   0.02943   0.01738  -0.0549   0.4291   1.0000
   6.250   1.0267   0.03007   0.01810  -0.0547   0.4252   1.0000
   6.500   1.0488   0.03121   0.01947  -0.0546   0.4200   1.0000
   6.750   1.0717   0.03220   0.02066  -0.0544   0.4151   1.0000
   7.000   1.0972   0.03283   0.02137  -0.0540   0.4106   1.0000
   7.250   1.1168   0.03402   0.02285  -0.0536   0.4033   1.0000
   7.500   1.1410   0.03460   0.02354  -0.0530   0.3968   1.0000
   7.750   1.1608   0.03567   0.02484  -0.0525   0.3895   1.0000
   8.000   1.1831   0.03646   0.02580  -0.0519   0.3827   1.0000
   8.250   1.2043   0.03742   0.02700  -0.0513   0.3764   1.0000
   8.500   1.2228   0.03853   0.02837  -0.0506   0.3687   1.0000
   8.750   1.2437   0.03924   0.02926  -0.0497   0.3604   1.0000
   9.000   1.2661   0.03956   0.02972  -0.0487   0.3503   1.0000
   9.250   1.2799   0.04059   0.03107  -0.0474   0.3388   1.0000
   9.500   1.2982   0.04106   0.03173  -0.0462   0.3273   1.0000
   9.750   1.3206   0.04106   0.03184  -0.0450   0.3158   1.0000
  10.000   1.3333   0.04175   0.03279  -0.0433   0.3026   1.0000
  10.250   1.3397   0.04286   0.03421  -0.0414   0.2890   1.0000
  10.500   1.3433   0.04423   0.03593  -0.0395   0.2762   1.0000
  10.750   1.3436   0.04579   0.03779  -0.0375   0.2634   1.0000
  11.000   1.3363   0.04775   0.04000  -0.0351   0.2507   1.0000
  11.250   1.3228   0.05059   0.04306  -0.0335   0.2380   1.0000
  11.500   1.3054   0.05464   0.04731  -0.0334   0.2250   1.0000
  11.750   1.2864   0.05961   0.05244  -0.0344   0.2114   1.0000
  12.000   1.2729   0.06409   0.05702  -0.0355   0.1947   1.0000
  12.250   1.2756   0.06559   0.05824  -0.0351   0.1681   1.0000
  12.500   1.2644   0.06969   0.06208  -0.0357   0.1500   1.0000
  12.750   1.2489   0.07493   0.06722  -0.0370   0.1366   1.0000
  13.000   1.2339   0.08034   0.07257  -0.0385   0.1248   1.0000
  13.250   1.2208   0.08551   0.07767  -0.0398   0.1144   1.0000
  13.500   1.2098   0.09028   0.08230  -0.0409   0.1053   1.0000
  13.750   1.1994   0.09542   0.08753  -0.0423   0.0966   1.0000
  14.000   1.1911   0.10016   0.09223  -0.0436   0.0889   1.0000
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