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GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 50,000
Max Cl/Cd: 35.42 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe315-il-50000.txt
Download as CSV file: xf-goe315-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3856   0.11354   0.10643  -0.0113   1.0000   0.1293
  -9.000  -0.3865   0.11168   0.10463  -0.0130   1.0000   0.1336
  -8.750  -0.3987   0.11160   0.10470  -0.0162   1.0000   0.1355
  -8.500  -0.3756   0.10484   0.09792  -0.0142   1.0000   0.1408
  -8.250  -0.3722   0.10218   0.09532  -0.0148   1.0000   0.1469
  -8.000  -0.3854   0.10164   0.09494  -0.0175   1.0000   0.1503
  -7.750  -0.3698   0.09652   0.08985  -0.0162   1.0000   0.1555
  -7.500  -0.3685   0.09407   0.08749  -0.0165   1.0000   0.1629
  -7.250  -0.3821   0.09387   0.08740  -0.0231   1.0000   0.1665
  -7.000  -0.3627   0.08826   0.08184  -0.0179   1.0000   0.1779
  -6.500  -0.3608   0.08333   0.07708  -0.0216   1.0000   0.1962
  -6.250  -0.3507   0.07939   0.07321  -0.0190   1.0000   0.2058
  -6.000  -0.3486   0.07663   0.07054  -0.0200   1.0000   0.2166
  -5.750  -0.3462   0.07409   0.06808  -0.0207   1.0000   0.2303
  -5.500  -0.3421   0.07133   0.06542  -0.0197   1.0000   0.2460
  -5.250  -0.3379   0.06856   0.06276  -0.0173   1.0000   0.2639
  -5.000  -0.3365   0.06628   0.06059  -0.0150   1.0000   0.2855
  -4.750   0.0413   0.04221   0.03550  -0.0231   1.0000   1.0000
  -4.500   0.0525   0.04041   0.03377  -0.0239   1.0000   1.0000
  -4.250   0.0636   0.03866   0.03211  -0.0247   1.0000   1.0000
  -4.000   0.0744   0.03701   0.03056  -0.0254   1.0000   1.0000
  -3.750   0.0848   0.03543   0.02908  -0.0260   1.0000   1.0000
  -3.500   0.0611   0.03602   0.02987  -0.0187   1.0000   0.9846
  -3.250   0.0083   0.03774   0.03191  -0.0057   1.0000   0.9471
  -3.000  -0.0417   0.03894   0.03345   0.0052   1.0000   0.9147
  -2.750  -0.0959   0.04029   0.03511   0.0161   1.0000   0.8961
  -2.500  -0.1520   0.04157   0.03662   0.0266   1.0000   0.8811
  -2.250  -0.2202   0.04288   0.03817   0.0386   1.0000   0.8633
  -2.000  -0.3843   0.04575   0.04142   0.0576   0.9950   0.7651
  -1.750  -0.3474   0.04264   0.03824   0.0455   0.9785   0.7493
  -1.500  -0.0603   0.03631   0.02874  -0.0437   0.9587   0.3206
  -1.250   0.0025   0.03551   0.02695  -0.0498   0.9461   0.2414
  -1.000   0.0508   0.03455   0.02545  -0.0532   0.9339   0.2086
  -0.750   0.0966   0.03370   0.02417  -0.0562   0.9225   0.1931
  -0.500   0.1481   0.03293   0.02295  -0.0599   0.9116   0.1792
  -0.250   0.1855   0.03227   0.02205  -0.0615   0.8991   0.1709
   0.000   0.2232   0.03203   0.02148  -0.0629   0.8868   0.1655
   0.250   0.2668   0.03144   0.02075  -0.0653   0.8753   0.1643
   0.500   0.3268   0.03057   0.01977  -0.0701   0.8649   0.1701
   0.750   0.3631   0.03027   0.01943  -0.0713   0.8515   0.1743
   1.000   0.3999   0.03005   0.01915  -0.0723   0.8375   0.1802
   1.250   0.4370   0.02969   0.01882  -0.0733   0.8231   0.1939
   1.500   0.4745   0.02910   0.01850  -0.0743   0.8081   0.2379
   1.750   0.5348   0.02708   0.01789  -0.0779   0.7928   1.0000
   2.000   0.5656   0.02742   0.01786  -0.0773   0.7769   1.0000
   2.250   0.5941   0.02781   0.01806  -0.0765   0.7610   1.0000
   2.500   0.6212   0.02822   0.01834  -0.0756   0.7448   1.0000
   2.750   0.6472   0.02866   0.01868  -0.0744   0.7286   1.0000
   3.000   0.6725   0.02911   0.01908  -0.0732   0.7122   1.0000
   3.250   0.6975   0.02956   0.01947  -0.0718   0.6955   1.0000
   3.500   0.7226   0.02995   0.01983  -0.0703   0.6786   1.0000
   3.750   0.7475   0.03034   0.02019  -0.0688   0.6618   1.0000
   4.000   0.7728   0.03067   0.02052  -0.0672   0.6451   1.0000
   4.250   0.7916   0.03149   0.02136  -0.0656   0.6261   1.0000
   4.500   0.8123   0.03223   0.02214  -0.0640   0.6082   1.0000
   4.750   0.8344   0.03290   0.02284  -0.0626   0.5913   1.0000
   5.000   0.8567   0.03361   0.02360  -0.0612   0.5753   1.0000
   5.250   0.8783   0.03446   0.02450  -0.0599   0.5602   1.0000
   5.500   0.8992   0.03552   0.02563  -0.0587   0.5466   1.0000
   5.750   0.9243   0.03621   0.02637  -0.0576   0.5348   1.0000
   6.000   0.9452   0.03733   0.02761  -0.0566   0.5226   1.0000
   6.250   0.9555   0.03961   0.03005  -0.0556   0.5098   1.0000
   6.500   0.9684   0.04162   0.03219  -0.0546   0.4983   1.0000
   6.750   0.9921   0.04208   0.03275  -0.0531   0.4856   1.0000
   7.000   1.0188   0.04184   0.03262  -0.0513   0.4708   1.0000
   7.250   1.0435   0.04159   0.03247  -0.0494   0.4548   1.0000
   7.500   1.0677   0.04119   0.03217  -0.0473   0.4379   1.0000
   7.750   1.0928   0.04078   0.03192  -0.0455   0.4220   1.0000
   8.000   1.1268   0.03862   0.02978  -0.0432   0.4013   1.0000
   8.250   1.1536   0.03660   0.02779  -0.0405   0.3755   1.0000
   8.500   1.1770   0.03468   0.02587  -0.0376   0.3460   1.0000
   8.750   1.1929   0.03368   0.02488  -0.0344   0.3121   1.0000
   9.000   1.1954   0.03375   0.02471  -0.0301   0.2616   1.0000
   9.250   1.1882   0.03569   0.02628  -0.0257   0.2082   1.0000
   9.500   1.1882   0.03780   0.02807  -0.0225   0.1767   1.0000
   9.750   1.1934   0.03983   0.03000  -0.0201   0.1576   1.0000
  10.000   1.2040   0.04181   0.03191  -0.0182   0.1448   1.0000
  10.250   1.2233   0.04379   0.03373  -0.0170   0.1351   1.0000
  10.500   1.2382   0.04629   0.03654  -0.0156   0.1278   1.0000
  10.750   1.2591   0.04864   0.03881  -0.0149   0.1208   1.0000
  11.000   1.2688   0.05164   0.04218  -0.0134   0.1165   1.0000
  11.250   1.2822   0.05484   0.04562  -0.0124   0.1135   1.0000
  11.500   1.3065   0.05840   0.04916  -0.0124   0.1098   1.0000
  11.750   1.2963   0.06203   0.05323  -0.0100   0.1089   1.0000
  12.000   1.2796   0.06579   0.05733  -0.0078   0.1084   1.0000
  12.250   1.2606   0.07009   0.06192  -0.0066   0.1083   1.0000
  12.500   1.2378   0.07503   0.06712  -0.0065   0.1084   1.0000
  12.750   1.2131   0.08078   0.07309  -0.0077   0.1089   1.0000
  13.000   1.1877   0.08734   0.07981  -0.0099   0.1095   1.0000
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