Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.89 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe318-il-1000000.txt
Download as CSV file: xf-goe318-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3743   0.09493   0.09270   0.0061   0.7067   0.0161
  -8.750  -0.3740   0.09057   0.08833   0.0047   0.7007   0.0161
  -8.500  -0.4778   0.09916   0.09691   0.0152   0.7204   0.0161
  -8.250  -0.4743   0.09502   0.09273   0.0126   0.7124   0.0161
  -8.000  -0.4713   0.09071   0.08842   0.0096   0.7047   0.0161
  -7.750  -0.3585   0.07703   0.07472   0.0023   0.6775   0.0172
  -7.500  -0.3557   0.07363   0.07132   0.0010   0.6724   0.0176
  -7.250  -0.3547   0.06992   0.06758  -0.0009   0.6679   0.0182
  -7.000  -0.4318   0.07672   0.07431  -0.0021   0.6786   0.0173
  -6.750  -0.3515   0.05685   0.05447  -0.0155   0.6615   0.0199
  -6.500  -0.3407   0.05071   0.04826  -0.0205   0.6577   0.0199
  -6.250  -0.3277   0.04403   0.04147  -0.0253   0.6542   0.0200
  -4.750  -0.2133   0.01513   0.01150  -0.0379   0.6288   0.0255
  -4.500  -0.1894   0.01419   0.01048  -0.0382   0.6239   0.0259
  -4.250  -0.1648   0.01306   0.00926  -0.0385   0.6195   0.0266
  -4.000  -0.1395   0.01152   0.00758  -0.0388   0.6150   0.0278
  -3.750  -0.1094   0.01045   0.00611  -0.0383   0.6103   0.0306
  -3.500  -0.0836   0.00883   0.00417  -0.0384   0.6061   0.0307
  -2.750  -0.0064   0.01454   0.00870  -0.0397   0.5974   0.0314
  -2.500   0.0223   0.01376   0.00775  -0.0397   0.5918   0.0312
  -2.250   0.0511   0.01307   0.00696  -0.0397   0.5864   0.0311
  -2.000   0.0799   0.01244   0.00623  -0.0398   0.5802   0.0310
  -1.750   0.1087   0.01179   0.00547  -0.0398   0.5741   0.0309
  -1.500   0.1374   0.01098   0.00459  -0.0398   0.5680   0.0310
  -1.250   0.1658   0.01010   0.00366  -0.0399   0.5624   0.0318
  -1.000   0.1945   0.00968   0.00322  -0.0400   0.5570   0.0325
  -0.750   0.2233   0.00937   0.00290  -0.0401   0.5508   0.0331
  -0.250   0.2811   0.00892   0.00240  -0.0403   0.5378   0.0344
   0.000   0.3100   0.00875   0.00219  -0.0404   0.5303   0.0350
   0.250   0.3390   0.00858   0.00201  -0.0405   0.5227   0.0356
   0.500   0.3680   0.00847   0.00185  -0.0406   0.5141   0.0365
   0.750   0.3970   0.00838   0.00176  -0.0408   0.5048   0.0376
   1.000   0.4260   0.00834   0.00168  -0.0409   0.4951   0.0384
   1.250   0.4551   0.00820   0.00148  -0.0411   0.4842   0.0411
   1.500   0.4841   0.00817   0.00142  -0.0412   0.4725   0.0439
   1.750   0.5130   0.00817   0.00139  -0.0414   0.4601   0.0474
   2.000   0.5420   0.00802   0.00140  -0.0417   0.4469   0.1333
   2.250   0.5658   0.00602   0.00152  -0.0414   0.4340   1.0000
   2.500   0.5945   0.00616   0.00156  -0.0416   0.4193   1.0000
   2.750   0.6232   0.00631   0.00163  -0.0417   0.4042   1.0000
   3.000   0.6519   0.00647   0.00170  -0.0419   0.3881   1.0000
   3.250   0.6805   0.00666   0.00179  -0.0421   0.3699   1.0000
   3.500   0.7089   0.00688   0.00190  -0.0423   0.3498   1.0000
   3.750   0.7373   0.00711   0.00203  -0.0426   0.3269   1.0000
   4.000   0.7655   0.00739   0.00218  -0.0428   0.3047   1.0000
   4.250   0.7937   0.00764   0.00234  -0.0430   0.2867   1.0000
   4.500   0.8220   0.00787   0.00251  -0.0432   0.2742   1.0000
   4.750   0.8502   0.00809   0.00268  -0.0434   0.2651   1.0000
   5.000   0.8784   0.00827   0.00283  -0.0436   0.2587   1.0000
   5.250   0.9066   0.00847   0.00301  -0.0437   0.2531   1.0000
   5.500   0.9346   0.00868   0.00320  -0.0439   0.2478   1.0000
   5.750   0.9628   0.00883   0.00335  -0.0441   0.2434   1.0000
   6.000   0.9907   0.00904   0.00354  -0.0443   0.2381   1.0000
   6.250   1.0185   0.00925   0.00374  -0.0444   0.2325   1.0000
   6.500   1.0465   0.00939   0.00391  -0.0446   0.2295   1.0000
   6.750   1.0743   0.00959   0.00410  -0.0447   0.2247   1.0000
   7.000   1.1018   0.00983   0.00434  -0.0449   0.2183   1.0000
   7.250   1.1296   0.00997   0.00451  -0.0450   0.2145   1.0000
   7.500   1.1570   0.01020   0.00473  -0.0452   0.2079   1.0000
   7.750   1.1844   0.01040   0.00495  -0.0453   0.2014   1.0000
   8.000   1.2114   0.01068   0.00519  -0.0454   0.1904   1.0000
   8.250   1.2376   0.01108   0.00547  -0.0455   0.1625   1.0000
   8.500   1.2539   0.01323   0.00697  -0.0451   0.0622   1.0000
   8.750   1.2750   0.01440   0.00793  -0.0448   0.0297   1.0000
   9.000   1.2981   0.01516   0.00863  -0.0446   0.0200   1.0000
   9.250   1.3214   0.01584   0.00933  -0.0443   0.0168   1.0000
   9.500   1.3453   0.01638   0.00991  -0.0441   0.0157   1.0000
   9.750   1.3681   0.01702   0.01060  -0.0438   0.0145   1.0000
  10.000   1.3882   0.01798   0.01162  -0.0433   0.0132   1.0000
  10.250   1.4101   0.01863   0.01233  -0.0429   0.0127   1.0000
  10.500   1.4313   0.01930   0.01306  -0.0425   0.0121   1.0000
  10.750   1.4513   0.02005   0.01387  -0.0420   0.0115   1.0000
  11.000   1.4696   0.02092   0.01480  -0.0414   0.0109   1.0000
  11.250   1.4832   0.02217   0.01612  -0.0404   0.0104   1.0000
  11.500   1.4874   0.02405   0.01814  -0.0388   0.0099   1.0000
  11.750   1.4961   0.02526   0.01943  -0.0376   0.0098   1.0000
  12.000   1.5038   0.02694   0.02119  -0.0372   0.0096   1.0000
  12.250   1.5105   0.02894   0.02329  -0.0372   0.0094   1.0000
  12.500   1.5159   0.03119   0.02564  -0.0373   0.0092   1.0000
  12.750   1.5198   0.03365   0.02819  -0.0376   0.0089   1.0000
  13.000   1.5218   0.03636   0.03099  -0.0378   0.0087   1.0000
  13.250   1.5223   0.03928   0.03400  -0.0381   0.0086   1.0000
  13.500   1.5209   0.04241   0.03721  -0.0384   0.0084   1.0000
  13.750   1.5187   0.04564   0.04053  -0.0387   0.0083   1.0000
  14.000   1.5143   0.04918   0.04415  -0.0391   0.0081   1.0000
  14.250   1.5080   0.05297   0.04804  -0.0396   0.0080   1.0000
  14.500   1.4990   0.05717   0.05232  -0.0403   0.0079   1.0000
  14.750   1.4874   0.06178   0.05704  -0.0411   0.0078   1.0000
  15.000   1.4745   0.06677   0.06213  -0.0421   0.0076   1.0000
  15.250   1.4588   0.07226   0.06773  -0.0433   0.0075   1.0000
  15.500   1.4458   0.07743   0.07300  -0.0444   0.0074   1.0000
  15.750   1.4429   0.08145   0.07712  -0.0455   0.0073   1.0000
  16.000   1.4385   0.08569   0.08144  -0.0467   0.0073   1.0000
  16.250   1.4338   0.09001   0.08585  -0.0480   0.0072   1.0000
  16.500   1.4286   0.09443   0.09036  -0.0493   0.0071   1.0000
  16.750   1.4234   0.09889   0.09491  -0.0506   0.0071   1.0000
  17.000   1.4180   0.10336   0.09947  -0.0520   0.0070   1.0000
  17.250   1.4125   0.10792   0.10412  -0.0535   0.0069   1.0000
<< Back to GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)

Polar data table (+)

Polar graphs


<< Back to GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)