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GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 50,000
Max Cl/Cd: 20.69 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe318-il-50000.txt
Download as CSV file: xf-goe318-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4357   0.12164   0.11548   0.0118   1.0000   0.1431
  -9.000  -0.4409   0.12056   0.11449   0.0078   1.0000   0.1473
  -8.750  -0.4313   0.11581   0.10979   0.0069   1.0000   0.1505
  -8.500  -0.4171   0.11147   0.10547   0.0070   1.0000   0.1574
  -8.250  -0.4229   0.11025   0.10437   0.0024   1.0000   0.1627
  -8.000  -0.4080   0.10499   0.09916   0.0026   1.0000   0.1675
  -7.750  -0.4022   0.10212   0.09636   0.0006   1.0000   0.1762
  -7.500  -0.3983   0.09870   0.09306  -0.0020   1.0000   0.1818
  -7.250  -0.3915   0.09594   0.09037  -0.0052   1.0000   0.1928
  -6.500  -0.3658   0.08658   0.08122  -0.0177   1.0000   0.2251
  -6.250  -0.3487   0.08180   0.07652  -0.0139   1.0000   0.2371
  -6.000  -0.3422   0.07880   0.07361  -0.0145   1.0000   0.2483
  -5.500  -0.3669   0.07644   0.07143  -0.0106   1.0000   0.2634
  -5.250  -0.3800   0.07532   0.07036  -0.0103   1.0000   0.2737
  -5.000  -0.3861   0.07377   0.06883  -0.0094   1.0000   0.2881
  -4.500   0.0375   0.04273   0.03718  -0.0172   1.0000   1.0000
  -4.250   0.0550   0.04080   0.03531  -0.0209   1.0000   1.0000
  -4.000   0.0692   0.03926   0.03382  -0.0239   1.0000   1.0000
  -3.750   0.0763   0.03833   0.03295  -0.0254   1.0000   1.0000
  -3.500   0.0111   0.04168   0.03649  -0.0112   1.0000   0.9757
  -3.250  -0.0684   0.04516   0.04018   0.0053   1.0000   0.9433
  -3.000  -0.1131   0.04599   0.04112   0.0112   0.9834   0.8852
  -2.750  -0.1597   0.04639   0.04165   0.0157   0.9646   0.8337
  -2.500  -0.0264   0.04113   0.03348  -0.0675   0.9331   0.2399
  -2.250   0.0383   0.03821   0.02967  -0.0743   0.9254   0.1931
  -2.000   0.0750   0.03642   0.02757  -0.0765   0.9152   0.1847
  -1.750   0.1209   0.03498   0.02559  -0.0797   0.9061   0.1739
  -1.500   0.1679   0.03363   0.02377  -0.0828   0.8968   0.1673
  -1.250   0.2008   0.03303   0.02278  -0.0836   0.8859   0.1652
  -1.000   0.2371   0.03233   0.02197  -0.0851   0.8757   0.1703
  -0.750   0.2784   0.03179   0.02116  -0.0867   0.8657   0.1772
  -0.500   0.3079   0.03153   0.02079  -0.0868   0.8538   0.1824
  -0.250   0.3382   0.03138   0.02055  -0.0869   0.8419   0.1922
   0.000   0.3687   0.03112   0.02035  -0.0869   0.8297   0.2124
   0.250   0.3988   0.03059   0.02010  -0.0866   0.8163   0.2623
   0.500   0.4358   0.02846   0.01938  -0.0856   0.8027   1.0000
   0.750   0.4602   0.02906   0.01962  -0.0843   0.7865   1.0000
   1.000   0.4839   0.02964   0.01995  -0.0829   0.7704   1.0000
   1.250   0.5075   0.03022   0.02034  -0.0815   0.7548   1.0000
   1.500   0.5311   0.03081   0.02076  -0.0802   0.7398   1.0000
   1.750   0.5546   0.03140   0.02122  -0.0788   0.7252   1.0000
   2.000   0.5781   0.03196   0.02167  -0.0774   0.7107   1.0000
   2.250   0.6018   0.03247   0.02208  -0.0759   0.6963   1.0000
   2.500   0.6261   0.03286   0.02237  -0.0742   0.6824   1.0000
   2.750   0.6488   0.03344   0.02289  -0.0728   0.6672   1.0000
   3.000   0.6715   0.03399   0.02340  -0.0713   0.6518   1.0000
   3.250   0.6943   0.03454   0.02390  -0.0699   0.6365   1.0000
   3.500   0.7170   0.03516   0.02449  -0.0686   0.6212   1.0000
   3.750   0.7392   0.03594   0.02526  -0.0675   0.6062   1.0000
   4.000   0.7611   0.03681   0.02615  -0.0666   0.5913   1.0000
   4.250   0.7824   0.03781   0.02717  -0.0658   0.5767   1.0000
   4.500   0.8028   0.03902   0.02840  -0.0652   0.5627   1.0000
   4.750   0.8218   0.04055   0.02998  -0.0649   0.5494   1.0000
   5.000   0.8398   0.04236   0.03186  -0.0649   0.5379   1.0000
   5.250   0.8658   0.04289   0.03242  -0.0638   0.5307   1.0000
   5.500   0.8717   0.04691   0.03656  -0.0656   0.5191   1.0000
   5.750   0.9022   0.04685   0.03652  -0.0640   0.5145   1.0000
   6.000   0.8914   0.05329   0.04310  -0.0673   0.5034   1.0000
   6.250   0.9030   0.05620   0.04610  -0.0678   0.4976   1.0000
   6.500   0.8720   0.06459   0.05452  -0.0719   0.4931   1.0000
   6.750   0.8566   0.07015   0.06008  -0.0733   0.4929   1.0000
   7.000   0.8472   0.07512   0.06507  -0.0746   0.4942   1.0000
   7.250   0.8438   0.07951   0.06950  -0.0756   0.4960   1.0000
   7.500   0.8505   0.08336   0.07342  -0.0766   0.4985   1.0000
   7.750   0.7301   0.09856   0.08857  -0.0869   0.6257   1.0000
   8.000   0.7612   0.10258   0.09269  -0.0887   0.6209   1.0000
   8.250   0.7465   0.10386   0.09398  -0.0867   0.6126   1.0000
   8.500   0.7719   0.10746   0.09770  -0.0879   0.6064   1.0000
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