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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 100,000
Max Cl/Cd: 50.86 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe316-il-100000.txt
Download as CSV file: xf-goe316-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3873   0.10065   0.09602  -0.0066   1.0000   0.0620
  -8.000  -0.3830   0.09760   0.09303  -0.0091   1.0000   0.0639
  -7.750  -0.3822   0.09508   0.09057  -0.0136   1.0000   0.0657
  -7.500  -0.3755   0.09285   0.08833  -0.0263   1.0000   0.0669
  -7.250  -0.3661   0.08841   0.08389  -0.0312   1.0000   0.0676
  -7.000  -0.3578   0.08326   0.07886  -0.0237   1.0000   0.0695
  -6.750  -0.3471   0.07994   0.07559  -0.0233   1.0000   0.0723
  -6.500  -0.3354   0.07659   0.07225  -0.0261   1.0000   0.0757
  -6.250  -0.3142   0.07477   0.07015  -0.0385   1.0000   0.0807
  -6.000  -0.3067   0.06988   0.06534  -0.0387   1.0000   0.0819
  -5.750  -0.3036   0.06643   0.06207  -0.0355   1.0000   0.0834
  -5.500  -0.3066   0.06452   0.06025  -0.0328   1.0000   0.0851
  -5.250  -0.3139   0.06316   0.05893  -0.0301   1.0000   0.0868
  -5.000  -0.3004   0.06070   0.05638  -0.0321   0.9972   0.0916
  -4.750  -0.2539   0.05558   0.05104  -0.0409   0.9876   0.0995
  -4.500  -0.2043   0.05150   0.04661  -0.0495   0.9774   0.1122
  -4.250  -0.1554   0.04795   0.04274  -0.0566   0.9685   0.1262
  -4.000  -0.1120   0.04412   0.03874  -0.0619   0.9585   0.1413
  -3.750  -0.0758   0.04046   0.03508  -0.0653   0.9463   0.1583
  -3.500  -0.0415   0.03783   0.03232  -0.0683   0.9331   0.1882
  -3.250  -0.0129   0.03532   0.02980  -0.0696   0.9194   0.2210
  -3.000   0.0112   0.03325   0.02776  -0.0696   0.9047   0.2676
  -2.750   0.0316   0.03131   0.02589  -0.0682   0.8894   0.3156
  -2.500   0.0504   0.02950   0.02414  -0.0661   0.8738   0.3638
  -2.250   0.0680   0.02777   0.02249  -0.0633   0.8581   0.4134
  -2.000   0.0905   0.02610   0.02076  -0.0617   0.8424   0.4473
  -1.750   0.1347   0.02462   0.01862  -0.0656   0.8263   0.4033
  -1.500   0.2017   0.02383   0.01597  -0.0690   0.8113   0.1799
  -1.250   0.2341   0.02307   0.01460  -0.0672   0.7955   0.1358
  -1.000   0.2622   0.02243   0.01355  -0.0657   0.7790   0.1232
  -0.750   0.2883   0.02145   0.01240  -0.0645   0.7619   0.1206
  -0.500   0.3150   0.02066   0.01137  -0.0632   0.7444   0.1150
  -0.250   0.3419   0.02036   0.01076  -0.0617   0.7266   0.1109
   0.000   0.3680   0.01974   0.01001  -0.0606   0.7078   0.1099
   0.250   0.3941   0.01913   0.00933  -0.0596   0.6866   0.1098
   0.500   0.4194   0.01839   0.00860  -0.0585   0.6662   0.1131
   0.750   0.4446   0.01790   0.00809  -0.0574   0.6449   0.1183
   1.000   0.4704   0.01758   0.00766  -0.0564   0.6220   0.1220
   1.250   0.4965   0.01733   0.00721  -0.0555   0.6020   0.1273
   1.500   0.5236   0.01722   0.00695  -0.0550   0.5810   0.1389
   1.750   0.5512   0.01692   0.00675  -0.0547   0.5633   0.1934
   2.000   0.5799   0.01527   0.00662  -0.0541   0.5482   1.0000
   2.250   0.6071   0.01564   0.00669  -0.0537   0.5354   1.0000
   2.500   0.6342   0.01603   0.00680  -0.0534   0.5252   1.0000
   2.750   0.6614   0.01645   0.00713  -0.0534   0.5145   1.0000
   3.000   0.6887   0.01689   0.00745  -0.0533   0.5065   1.0000
   3.250   0.7160   0.01733   0.00781  -0.0533   0.4986   1.0000
   3.500   0.7432   0.01780   0.00819  -0.0532   0.4920   1.0000
   3.750   0.7703   0.01827   0.00868  -0.0532   0.4849   1.0000
   4.000   0.7977   0.01876   0.00906  -0.0532   0.4800   1.0000
   4.250   0.8246   0.01934   0.00973  -0.0533   0.4745   1.0000
   4.500   0.8516   0.01990   0.01033  -0.0534   0.4696   1.0000
   4.750   0.8788   0.02045   0.01087  -0.0534   0.4656   1.0000
   5.000   0.9053   0.02111   0.01161  -0.0534   0.4610   1.0000
   5.250   0.9315   0.02178   0.01241  -0.0535   0.4561   1.0000
   5.500   0.9582   0.02244   0.01314  -0.0536   0.4524   1.0000
   5.750   0.9852   0.02307   0.01375  -0.0535   0.4489   1.0000
   6.000   1.0096   0.02383   0.01476  -0.0535   0.4424   1.0000
   6.250   1.0360   0.02424   0.01517  -0.0532   0.4360   1.0000
   6.500   1.0608   0.02491   0.01600  -0.0530   0.4295   1.0000
   6.750   1.0860   0.02553   0.01675  -0.0528   0.4233   1.0000
   7.000   1.1125   0.02599   0.01719  -0.0526   0.4175   1.0000
   7.250   1.1356   0.02668   0.01814  -0.0522   0.4094   1.0000
   7.500   1.1623   0.02696   0.01839  -0.0518   0.4024   1.0000
   7.750   1.1853   0.02750   0.01915  -0.0513   0.3932   1.0000
   8.000   1.2100   0.02791   0.01963  -0.0509   0.3849   1.0000
   8.250   1.2353   0.02814   0.01995  -0.0503   0.3758   1.0000
   8.500   1.2575   0.02880   0.02083  -0.0498   0.3668   1.0000
   8.750   1.2847   0.02886   0.02084  -0.0493   0.3577   1.0000
   9.000   1.3069   0.02905   0.02121  -0.0484   0.3454   1.0000
   9.250   1.3288   0.02913   0.02147  -0.0475   0.3319   1.0000
   9.500   1.3511   0.02872   0.02108  -0.0464   0.3151   1.0000
   9.750   1.3700   0.02816   0.02061  -0.0449   0.2946   1.0000
  10.000   1.3853   0.02780   0.02055  -0.0431   0.2716   1.0000
  10.250   1.3976   0.02748   0.02058  -0.0410   0.2315   1.0000
  10.500   1.3928   0.02910   0.02158  -0.0378   0.1589   1.0000
  10.750   1.3796   0.03233   0.02451  -0.0344   0.1251   1.0000
  11.000   1.3651   0.03526   0.02735  -0.0310   0.1083   1.0000
  11.250   1.3523   0.03851   0.03058  -0.0289   0.0966   1.0000
  11.500   1.3402   0.04215   0.03422  -0.0279   0.0884   1.0000
  11.750   1.3298   0.04591   0.03797  -0.0275   0.0819   1.0000
  12.000   1.3235   0.04938   0.04148  -0.0269   0.0758   1.0000
  12.250   1.3189   0.05263   0.04466  -0.0263   0.0708   1.0000
  12.500   1.3209   0.05520   0.04723  -0.0248   0.0658   1.0000
  12.750   1.3273   0.05736   0.04938  -0.0233   0.0616   1.0000
  13.000   1.3492   0.05852   0.05039  -0.0198   0.0573   1.0000
  13.250   1.3531   0.06138   0.05351  -0.0191   0.0551   1.0000
  13.500   1.3573   0.06426   0.05656  -0.0184   0.0527   1.0000
  13.750   1.3629   0.06709   0.05948  -0.0177   0.0505   1.0000
  14.250   1.3869   0.07428   0.06688  -0.0149   0.0475   1.0000
  14.500   1.3755   0.07869   0.07157  -0.0155   0.0474   1.0000
  14.750   1.3619   0.08351   0.07668  -0.0165   0.0472   1.0000
  15.000   1.3463   0.08876   0.08220  -0.0180   0.0472   1.0000
  15.250   1.3286   0.09446   0.08815  -0.0201   0.0472   1.0000
  15.500   1.3097   0.10062   0.09455  -0.0228   0.0472   1.0000
  15.750   1.2897   0.10724   0.10137  -0.0260   0.0473   1.0000
  16.000   1.2694   0.11434   0.10867  -0.0296   0.0475   1.0000
  16.500   1.1998   0.13563   0.13058  -0.0458   0.0496   1.0000
  16.750   1.0887   0.17204   0.16718  -0.0712   0.0570   1.0000
  17.000   1.0790   0.18144   0.17656  -0.0758   0.0579   1.0000
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