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GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il)
Reynolds number: 500,000
Max Cl/Cd: 100.52 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe316-il-500000.txt
Download as CSV file: xf-goe316-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3219   0.09985   0.09783  -0.0081   1.0000   0.0204
  -9.250  -0.3155   0.09669   0.09469  -0.0084   1.0000   0.0207
  -9.000  -0.4323   0.10401   0.10190  -0.0038   1.0000   0.0201
  -8.750  -0.4218   0.10018   0.09808  -0.0016   1.0000   0.0203
  -8.500  -0.4135   0.09720   0.09511  -0.0019   1.0000   0.0206
  -8.250  -0.4062   0.09427   0.09220  -0.0031   1.0000   0.0209
  -8.000  -0.3997   0.09121   0.08917  -0.0048   1.0000   0.0214
  -7.750  -0.3939   0.08798   0.08597  -0.0069   1.0000   0.0220
  -7.500  -0.3882   0.08451   0.08253  -0.0099   1.0000   0.0226
  -7.250  -0.3757   0.07997   0.07799  -0.0168   1.0000   0.0238
  -6.750  -0.3255   0.06626   0.06407  -0.0397   0.9541   0.0245
  -6.500  -0.3180   0.06307   0.06081  -0.0385   0.9103   0.0248
  -6.250  -0.3077   0.06086   0.05847  -0.0375   0.8695   0.0251
  -6.000  -0.2923   0.05834   0.05579  -0.0383   0.8423   0.0257
  -5.750  -0.2729   0.05529   0.05259  -0.0403   0.8227   0.0265
  -5.500  -0.2499   0.05174   0.04885  -0.0431   0.8072   0.0279
  -5.250  -0.2094   0.04692   0.04350  -0.0480   0.7949   0.0297
  -5.000  -0.1935   0.04167   0.03811  -0.0495   0.7834   0.0302
  -4.750  -0.1734   0.03965   0.03600  -0.0498   0.7710   0.0307
  -4.500  -0.1505   0.03764   0.03389  -0.0504   0.7591   0.0315
  -4.250  -0.1254   0.03543   0.03152  -0.0511   0.7486   0.0327
  -4.000  -0.0898   0.03401   0.02960  -0.0511   0.7390   0.0361
  -3.750  -0.0655   0.02937   0.02462  -0.0519   0.7298   0.0369
  -3.500  -0.0416   0.02740   0.02260  -0.0524   0.7201   0.0376
  -3.250  -0.0161   0.02594   0.02103  -0.0527   0.7101   0.0385
  -3.000   0.0108   0.02454   0.01948  -0.0529   0.6995   0.0399
  -2.750   0.0395   0.02329   0.01800  -0.0528   0.6892   0.0426
  -2.500   0.0712   0.02385   0.01815  -0.0520   0.6779   0.0447
  -2.250   0.0964   0.01990   0.01405  -0.0527   0.6665   0.0466
  -2.000   0.1238   0.01887   0.01293  -0.0529   0.6535   0.0480
  -1.750   0.1519   0.01800   0.01191  -0.0530   0.6394   0.0503
  -1.500   0.1820   0.01884   0.01248  -0.0524   0.6226   0.0548
  -1.250   0.2093   0.01613   0.00954  -0.0528   0.6056   0.0574
  -1.000   0.2371   0.01540   0.00870  -0.0529   0.5859   0.0596
  -0.750   0.2654   0.01500   0.00814  -0.0528   0.5647   0.0636
  -0.500   0.2934   0.01431   0.00726  -0.0529   0.5437   0.0711
  -0.250   0.3215   0.01390   0.00673  -0.0529   0.5223   0.0755
   0.000   0.3524   0.01219   0.00455  -0.0517   0.5019   0.0458
   0.250   0.3803   0.01187   0.00410  -0.0517   0.4766   0.0456
   0.500   0.4079   0.01152   0.00363  -0.0516   0.4482   0.0461
   0.750   0.4355   0.01131   0.00332  -0.0516   0.4205   0.0477
   1.000   0.4633   0.01118   0.00309  -0.0516   0.4002   0.0486
   1.250   0.4912   0.01109   0.00292  -0.0517   0.3865   0.0498
   1.500   0.5193   0.01103   0.00280  -0.0517   0.3767   0.0514
   1.750   0.5475   0.01100   0.00273  -0.0518   0.3697   0.0532
   2.000   0.5756   0.01102   0.00271  -0.0518   0.3636   0.0550
   2.250   0.6036   0.01099   0.00263  -0.0519   0.3583   0.0610
   2.500   0.6320   0.01099   0.00263  -0.0519   0.3543   0.0669
   2.750   0.6562   0.00892   0.00277  -0.0516   0.3508   1.0000
   3.000   0.6841   0.00910   0.00284  -0.0516   0.3474   1.0000
   3.250   0.7117   0.00933   0.00298  -0.0516   0.3441   1.0000
   3.500   0.7396   0.00950   0.00312  -0.0516   0.3417   1.0000
   3.750   0.7676   0.00965   0.00327  -0.0516   0.3393   1.0000
   4.000   0.7955   0.00982   0.00343  -0.0517   0.3370   1.0000
   4.250   0.8232   0.01000   0.00359  -0.0517   0.3347   1.0000
   4.500   0.8507   0.01021   0.00376  -0.0517   0.3309   1.0000
   4.750   0.8781   0.01043   0.00396  -0.0517   0.3257   1.0000
   5.000   0.9059   0.01053   0.00409  -0.0518   0.3209   1.0000
   5.250   0.9334   0.01071   0.00425  -0.0518   0.3172   1.0000
   5.500   0.9605   0.01097   0.00450  -0.0518   0.3142   1.0000
   5.750   0.9878   0.01120   0.00474  -0.0518   0.3114   1.0000
   6.000   1.0154   0.01134   0.00494  -0.0518   0.3090   1.0000
   6.250   1.0429   0.01150   0.00515  -0.0518   0.3060   1.0000
   6.500   1.0701   0.01166   0.00533  -0.0518   0.3019   1.0000
   6.750   1.0966   0.01195   0.00560  -0.0518   0.2968   1.0000
   7.000   1.1242   0.01200   0.00575  -0.0518   0.2925   1.0000
   7.250   1.1515   0.01210   0.00590  -0.0519   0.2865   1.0000
   7.500   1.1781   0.01230   0.00611  -0.0518   0.2805   1.0000
   7.750   1.2056   0.01234   0.00625  -0.0519   0.2736   1.0000
   8.000   1.2322   0.01251   0.00644  -0.0518   0.2656   1.0000
   8.250   1.2592   0.01262   0.00660  -0.0518   0.2547   1.0000
   8.500   1.2857   0.01279   0.00677  -0.0518   0.2366   1.0000
   8.750   1.3087   0.01341   0.00714  -0.0515   0.1844   1.0000
   9.000   1.3268   0.01469   0.00812  -0.0507   0.1365   1.0000
   9.250   1.3452   0.01590   0.00910  -0.0499   0.0969   1.0000
   9.500   1.3617   0.01723   0.01020  -0.0489   0.0632   1.0000
   9.750   1.3814   0.01812   0.01108  -0.0482   0.0528   1.0000
  10.000   1.4007   0.01898   0.01198  -0.0473   0.0429   1.0000
  10.250   1.4172   0.02008   0.01301  -0.0462   0.0313   1.0000
  10.500   1.4336   0.02111   0.01402  -0.0451   0.0253   1.0000
  10.750   1.4496   0.02208   0.01507  -0.0438   0.0225   1.0000
  11.000   1.4628   0.02320   0.01622  -0.0424   0.0205   1.0000
  11.250   1.4714   0.02456   0.01770  -0.0404   0.0191   1.0000
  11.500   1.4785   0.02572   0.01896  -0.0381   0.0183   1.0000
  11.750   1.4827   0.02714   0.02049  -0.0360   0.0176   1.0000
  12.000   1.4854   0.02891   0.02237  -0.0344   0.0170   1.0000
  12.250   1.4858   0.03117   0.02474  -0.0334   0.0165   1.0000
  12.500   1.4825   0.03413   0.02781  -0.0330   0.0160   1.0000
  12.750   1.4751   0.03784   0.03164  -0.0331   0.0156   1.0000
  13.000   1.4636   0.04222   0.03616  -0.0336   0.0153   1.0000
  13.250   1.4599   0.04579   0.03986  -0.0341   0.0151   1.0000
  13.500   1.4567   0.04939   0.04358  -0.0347   0.0149   1.0000
  13.750   1.4516   0.05329   0.04760  -0.0355   0.0146   1.0000
  14.000   1.4455   0.05738   0.05181  -0.0363   0.0144   1.0000
  14.250   1.4387   0.06156   0.05611  -0.0372   0.0141   1.0000
  14.500   1.4316   0.06583   0.06048  -0.0382   0.0138   1.0000
  14.750   1.4240   0.07017   0.06492  -0.0391   0.0136   1.0000
  15.000   1.4173   0.07450   0.06935  -0.0402   0.0134   1.0000
  15.250   1.4110   0.07886   0.07379  -0.0413   0.0131   1.0000
  15.500   1.4050   0.08317   0.07818  -0.0424   0.0129   1.0000
  15.750   1.3994   0.08742   0.08251  -0.0435   0.0128   1.0000
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