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GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 200,000
Max Cl/Cd: 70.01 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe318-il-200000-n5.txt
Download as CSV file: xf-goe318-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4529   0.11711   0.11396   0.0123   0.8907   0.0263
  -9.250  -0.4521   0.11385   0.11059   0.0108   0.8537   0.0263
  -9.000  -0.4489   0.11022   0.10690   0.0092   0.8324   0.0264
  -8.750  -0.4450   0.10647   0.10309   0.0074   0.8163   0.0264
  -8.500  -0.4408   0.10264   0.09921   0.0055   0.8028   0.0264
  -8.250  -0.4359   0.09875   0.09526   0.0036   0.7910   0.0264
  -7.750  -0.4256   0.09108   0.08752  -0.0001   0.7710   0.0262
  -7.250  -0.4078   0.08462   0.08099  -0.0023   0.7537   0.0285
  -7.000  -0.3933   0.07703   0.07328  -0.0141   0.7468   0.0262
  -6.750  -0.3804   0.07283   0.06902  -0.0170   0.7396   0.0260
  -6.500  -0.3632   0.06757   0.06363  -0.0223   0.7330   0.0260
  -6.250  -0.3487   0.06577   0.06181  -0.0225   0.7256   0.0285
  -6.000  -0.3288   0.06290   0.05884  -0.0252   0.7193   0.0312
  -5.750  -0.3057   0.05802   0.05380  -0.0300   0.7129   0.0320
  -5.500  -0.2830   0.05313   0.04870  -0.0338   0.7075   0.0311
  -5.250  -0.2577   0.04836   0.04370  -0.0372   0.7017   0.0312
  -5.000  -0.2290   0.04344   0.03844  -0.0404   0.6961   0.0330
  -4.750  -0.2025   0.03895   0.03359  -0.0423   0.6914   0.0332
  -4.500  -0.1747   0.03462   0.02884  -0.0438   0.6859   0.0336
  -4.250  -0.1472   0.03040   0.02407  -0.0449   0.6807   0.0354
  -4.000  -0.1206   0.02772   0.02100  -0.0453   0.6759   0.0356
  -3.750  -0.0932   0.02551   0.01847  -0.0457   0.6703   0.0359
  -3.500  -0.0657   0.02381   0.01650  -0.0459   0.6648   0.0364
  -3.250  -0.0386   0.02287   0.01540  -0.0461   0.6601   0.0377
  -3.000  -0.0102   0.02165   0.01395  -0.0463   0.6544   0.0387
  -2.750   0.0185   0.02021   0.01219  -0.0463   0.6490   0.0388
  -2.500   0.0470   0.01908   0.01075  -0.0462   0.6437   0.0391
  -2.250   0.0758   0.01811   0.00958  -0.0463   0.6365   0.0396
  -2.000   0.1041   0.01732   0.00855  -0.0461   0.6301   0.0401
  -1.750   0.1328   0.01662   0.00771  -0.0461   0.6224   0.0406
  -1.500   0.1611   0.01611   0.00707  -0.0460   0.6155   0.0420
  -1.250   0.1896   0.01564   0.00650  -0.0460   0.6083   0.0432
  -1.000   0.2179   0.01514   0.00591  -0.0459   0.6013   0.0437
  -0.750   0.2462   0.01469   0.00540  -0.0459   0.5941   0.0441
  -0.500   0.2745   0.01430   0.00496  -0.0458   0.5859   0.0446
  -0.250   0.3028   0.01398   0.00460  -0.0458   0.5772   0.0452
   0.000   0.3309   0.01355   0.00415  -0.0458   0.5690   0.0464
   0.250   0.3594   0.01326   0.00387  -0.0458   0.5610   0.0481
   0.500   0.3877   0.01308   0.00364  -0.0459   0.5536   0.0501
   0.750   0.4164   0.01294   0.00349  -0.0460   0.5450   0.0540
   1.000   0.4448   0.01284   0.00333  -0.0460   0.5372   0.0582
   1.250   0.4735   0.01269   0.00323  -0.0461   0.5282   0.0657
   1.500   0.5018   0.01243   0.00320  -0.0462   0.5195   0.1443
   2.000   0.5560   0.01045   0.00317  -0.0458   0.4998   1.0000
   2.250   0.5842   0.01055   0.00317  -0.0458   0.4891   1.0000
   2.500   0.6123   0.01068   0.00318  -0.0458   0.4777   1.0000
   2.750   0.6403   0.01081   0.00323  -0.0459   0.4651   1.0000
   3.000   0.6684   0.01096   0.00331  -0.0459   0.4521   1.0000
   3.250   0.6963   0.01113   0.00339  -0.0459   0.4385   1.0000
   3.500   0.7240   0.01133   0.00351  -0.0460   0.4243   1.0000
   3.750   0.7517   0.01154   0.00365  -0.0460   0.4094   1.0000
   4.000   0.7792   0.01178   0.00381  -0.0461   0.3938   1.0000
   4.250   0.8066   0.01204   0.00400  -0.0461   0.3778   1.0000
   4.500   0.8339   0.01233   0.00422  -0.0462   0.3620   1.0000
   4.750   0.8611   0.01262   0.00446  -0.0463   0.3473   1.0000
   5.000   0.8882   0.01293   0.00472  -0.0463   0.3342   1.0000
   5.250   0.9151   0.01325   0.00502  -0.0463   0.3228   1.0000
   5.500   0.9419   0.01359   0.00533  -0.0464   0.3133   1.0000
   5.750   0.9686   0.01393   0.00566  -0.0464   0.3049   1.0000
   6.000   0.9952   0.01428   0.00602  -0.0464   0.2985   1.0000
   6.250   1.0218   0.01462   0.00639  -0.0464   0.2926   1.0000
   6.500   1.0480   0.01500   0.00679  -0.0464   0.2879   1.0000
   6.750   1.0743   0.01537   0.00721  -0.0463   0.2841   1.0000
   7.000   1.1006   0.01572   0.00764  -0.0463   0.2797   1.0000
   7.250   1.1262   0.01614   0.00808  -0.0462   0.2740   1.0000
   7.500   1.1518   0.01654   0.00853  -0.0461   0.2679   1.0000
   7.750   1.1770   0.01695   0.00901  -0.0460   0.2592   1.0000
   8.000   1.2018   0.01737   0.00948  -0.0459   0.2483   1.0000
   8.250   1.2260   0.01786   0.00998  -0.0458   0.2375   1.0000
   8.500   1.2500   0.01833   0.01051  -0.0456   0.2265   1.0000
   8.750   1.2739   0.01880   0.01107  -0.0454   0.2125   1.0000
   9.000   1.2969   0.01936   0.01166  -0.0452   0.1950   1.0000
   9.500   1.3196   0.02315   0.01466  -0.0436   0.0612   1.0000
   9.750   1.3307   0.02487   0.01631  -0.0425   0.0402   1.0000
  10.000   1.3419   0.02640   0.01789  -0.0415   0.0298   1.0000
  10.250   1.3516   0.02793   0.01949  -0.0404   0.0250   1.0000
  10.500   1.3561   0.02963   0.02127  -0.0389   0.0223   1.0000
  10.750   1.3586   0.03172   0.02347  -0.0381   0.0206   1.0000
  11.000   1.3623   0.03396   0.02586  -0.0379   0.0193   1.0000
  11.250   1.3641   0.03652   0.02856  -0.0378   0.0183   1.0000
  11.500   1.3640   0.03940   0.03157  -0.0379   0.0176   1.0000
  11.750   1.3613   0.04264   0.03494  -0.0382   0.0169   1.0000
  12.000   1.3559   0.04628   0.03870  -0.0386   0.0164   1.0000
  12.250   1.3476   0.05032   0.04287  -0.0391   0.0160   1.0000
  12.500   1.3414   0.05416   0.04685  -0.0396   0.0156   1.0000
  12.750   1.3367   0.05787   0.05070  -0.0402   0.0153   1.0000
  13.000   1.3312   0.06172   0.05469  -0.0408   0.0149   1.0000
  13.250   1.3253   0.06569   0.05878  -0.0414   0.0145   1.0000
  13.500   1.3194   0.06973   0.06294  -0.0422   0.0141   1.0000
  13.750   1.3137   0.07390   0.06723  -0.0431   0.0137   1.0000
  14.000   1.3087   0.07810   0.07153  -0.0441   0.0134   1.0000
  14.250   1.3038   0.08231   0.07584  -0.0451   0.0131   1.0000
  14.500   1.2992   0.08649   0.08011  -0.0462   0.0128   1.0000
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