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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 50,000
Max Cl/Cd: 36.78 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe314-il-50000-n5.txt
Download as CSV file: xf-goe314-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3220   0.10978   0.10267  -0.0236   1.0000   0.0871
  -8.500  -0.3303   0.10917   0.10218  -0.0254   1.0000   0.0880
  -8.250  -0.3410   0.10855   0.10171  -0.0270   1.0000   0.0884
  -8.000  -0.3131   0.10108   0.09420  -0.0239   1.0000   0.0916
  -7.750  -0.3098   0.09839   0.09158  -0.0234   1.0000   0.0940
  -7.500  -0.3111   0.09623   0.08952  -0.0231   1.0000   0.0962
  -7.250  -0.3140   0.09429   0.08769  -0.0237   1.0000   0.0987
  -7.000  -0.3189   0.09308   0.08658  -0.0265   1.0000   0.1008
  -6.750  -0.3216   0.09216   0.08570  -0.0306   1.0000   0.1017
  -6.500  -0.3143   0.08739   0.08104  -0.0271   1.0000   0.1031
  -6.250  -0.3090   0.08420   0.07792  -0.0247   1.0000   0.1058
  -6.000  -0.3068   0.08192   0.07571  -0.0242   1.0000   0.1098
  -5.750  -0.3064   0.08101   0.07478  -0.0278   1.0000   0.1147
  -5.500  -0.3044   0.07810   0.07193  -0.0272   1.0000   0.1165
  -5.250  -0.3025   0.07512   0.06906  -0.0239   1.0000   0.1196
  -5.000  -0.2992   0.07298   0.06694  -0.0231   1.0000   0.1238
  -4.750  -0.2888   0.07208   0.06584  -0.0279   1.0000   0.1302
  -4.500  -0.2750   0.06770   0.06160  -0.0268   0.9956   0.1332
  -4.250  -0.2312   0.06456   0.05816  -0.0358   0.9838   0.1460
  -4.000  -0.2040   0.06038   0.05404  -0.0375   0.9738   0.1524
  -3.750  -0.1700   0.05710   0.05065  -0.0422   0.9619   0.1681
  -3.500  -0.1364   0.05425   0.04763  -0.0468   0.9491   0.1950
  -2.500   0.0483   0.04195   0.03352  -0.0655   0.9019   0.1013
  -2.250   0.0826   0.03917   0.03067  -0.0676   0.8889   0.0986
  -2.000   0.1199   0.03696   0.02819  -0.0696   0.8755   0.0966
  -1.500   0.1974   0.03321   0.02355  -0.0726   0.8476   0.0871
  -1.250   0.2322   0.03153   0.02162  -0.0736   0.8321   0.0857
  -1.000   0.2659   0.03011   0.01991  -0.0741   0.8154   0.0848
  -0.750   0.2984   0.02894   0.01844  -0.0742   0.7975   0.0855
  -0.500   0.3304   0.02806   0.01718  -0.0741   0.7788   0.0878
  -0.250   0.3612   0.02707   0.01594  -0.0739   0.7598   0.0892
   0.000   0.3919   0.02614   0.01480  -0.0737   0.7406   0.0896
   0.250   0.4203   0.02538   0.01385  -0.0731   0.7206   0.0906
   0.500   0.4501   0.02475   0.01302  -0.0726   0.6999   0.0921
   0.750   0.4799   0.02424   0.01232  -0.0722   0.6802   0.0959
   1.000   0.5086   0.02390   0.01171  -0.0716   0.6615   0.1014
   1.250   0.5362   0.02341   0.01114  -0.0710   0.6438   0.1055
   1.500   0.5623   0.02313   0.01071  -0.0701   0.6264   0.1096
   1.750   0.5881   0.02296   0.01039  -0.0693   0.6098   0.1163
   2.000   0.6136   0.02280   0.01014  -0.0685   0.5940   0.1281
   2.250   0.6395   0.02269   0.00997  -0.0678   0.5793   0.1403
   2.500   0.6651   0.02259   0.00994  -0.0672   0.5648   0.1672
   2.750   0.7054   0.02104   0.00988  -0.0694   0.5493   1.0000
   3.000   0.7300   0.02144   0.01001  -0.0685   0.5354   1.0000
   3.250   0.7543   0.02185   0.01020  -0.0676   0.5219   1.0000
   3.500   0.7786   0.02227   0.01045  -0.0668   0.5089   1.0000
   3.750   0.8029   0.02269   0.01072  -0.0659   0.4963   1.0000
   4.000   0.8271   0.02312   0.01101  -0.0651   0.4840   1.0000
   4.250   0.8499   0.02361   0.01145  -0.0641   0.4711   1.0000
   4.500   0.8730   0.02411   0.01191  -0.0633   0.4591   1.0000
   4.750   0.8968   0.02460   0.01232  -0.0624   0.4482   1.0000
   5.000   0.9200   0.02512   0.01281  -0.0616   0.4372   1.0000
   5.250   0.9423   0.02571   0.01345  -0.0606   0.4261   1.0000
   5.500   0.9658   0.02626   0.01396  -0.0598   0.4165   1.0000
   5.750   0.9881   0.02687   0.01462  -0.0589   0.4063   1.0000
   6.000   1.0100   0.02753   0.01534  -0.0580   0.3965   1.0000
   6.250   1.0336   0.02811   0.01593  -0.0573   0.3880   1.0000
   6.500   1.0541   0.02892   0.01689  -0.0563   0.3787   1.0000
   6.750   1.0781   0.02954   0.01750  -0.0556   0.3715   1.0000
   7.000   1.0972   0.03047   0.01863  -0.0545   0.3625   1.0000
   7.250   1.1209   0.03106   0.01924  -0.0538   0.3555   1.0000
   7.500   1.1381   0.03202   0.02042  -0.0525   0.3460   1.0000
   7.750   1.1606   0.03256   0.02096  -0.0516   0.3385   1.0000
   8.000   1.1768   0.03353   0.02217  -0.0502   0.3294   1.0000
   8.250   1.1981   0.03412   0.02283  -0.0492   0.3222   1.0000
   8.500   1.2134   0.03520   0.02417  -0.0478   0.3143   1.0000
   8.750   1.2360   0.03572   0.02472  -0.0469   0.3082   1.0000
   9.000   1.2474   0.03701   0.02632  -0.0452   0.3002   1.0000
   9.250   1.2682   0.03738   0.02676  -0.0441   0.2931   1.0000
   9.500   1.2774   0.03872   0.02842  -0.0421   0.2852   1.0000
   9.750   1.2955   0.03941   0.02924  -0.0409   0.2791   1.0000
  10.000   1.3064   0.04076   0.03086  -0.0392   0.2734   1.0000
  10.250   1.3167   0.04204   0.03240  -0.0374   0.2673   1.0000
  10.500   1.3320   0.04268   0.03321  -0.0358   0.2607   1.0000
  10.750   1.3324   0.04429   0.03512  -0.0333   0.2530   1.0000
  11.000   1.3419   0.04497   0.03594  -0.0311   0.2452   1.0000
  11.250   1.3355   0.04667   0.03788  -0.0280   0.2374   1.0000
  11.500   1.3345   0.04795   0.03929  -0.0254   0.2291   1.0000
  11.750   1.3278   0.04995   0.04148  -0.0232   0.2212   1.0000
  12.000   1.3189   0.05246   0.04418  -0.0216   0.2137   1.0000
  12.250   1.3133   0.05469   0.04654  -0.0204   0.2047   1.0000
  12.500   1.2916   0.05947   0.05153  -0.0205   0.1978   1.0000
  12.750   1.2837   0.06248   0.05461  -0.0205   0.1869   1.0000
  13.000   1.2549   0.06953   0.06189  -0.0227   0.1809   1.0000
  13.250   1.2410   0.07433   0.06676  -0.0241   0.1702   1.0000
  13.500   1.2287   0.07904   0.07151  -0.0257   0.1579   1.0000
  13.750   1.1940   0.08875   0.08138  -0.0299   0.1522   1.0000
  14.000   1.1794   0.09453   0.08720  -0.0321   0.1409   1.0000
  14.250   1.1677   0.09989   0.09255  -0.0343   0.1293   1.0000
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