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


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 50,000
Max Cl/Cd: 38.01 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe315-il-50000-n5.txt
Download as CSV file: xf-goe315-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3693   0.11038   0.10330  -0.0173   1.0000   0.0875
  -8.750  -0.3775   0.10964   0.10269  -0.0206   1.0000   0.0889
  -8.500  -0.3858   0.10855   0.10172  -0.0237   1.0000   0.0893
  -8.250  -0.3568   0.10080   0.09392  -0.0196   1.0000   0.0933
  -8.000  -0.3517   0.09783   0.09101  -0.0199   1.0000   0.0962
  -7.750  -0.3513   0.09536   0.08863  -0.0208   1.0000   0.0994
  -7.500  -0.3556   0.09355   0.08693  -0.0240   1.0000   0.1025
  -7.250  -0.3586   0.09221   0.08564  -0.0304   1.0000   0.1038
  -7.000  -0.3478   0.08715   0.08069  -0.0274   1.0000   0.1058
  -6.750  -0.3387   0.08371   0.07731  -0.0257   1.0000   0.1102
  -6.500  -0.3347   0.08128   0.07493  -0.0282   1.0000   0.1160
  -6.000  -0.3233   0.07514   0.06893  -0.0287   1.0000   0.1252
  -5.750  -0.3180   0.07414   0.06780  -0.0349   1.0000   0.1337
  -5.500  -0.3124   0.06978   0.06363  -0.0310   1.0000   0.1366
  -5.250  -0.3075   0.06727   0.06119  -0.0296   1.0000   0.1419
  -5.000  -0.3045   0.06543   0.05929  -0.0313   1.0000   0.1506
  -4.750  -0.2984   0.06259   0.05655  -0.0293   0.9978   0.1553
  -4.500  -0.2648   0.05877   0.05261  -0.0348   0.9836   0.1726
  -4.250  -0.2350   0.05529   0.04905  -0.0390   0.9685   0.2013
  -3.500  -0.0890   0.04415   0.03617  -0.0576   0.9286   0.1031
  -3.000  -0.0119   0.03845   0.02967  -0.0629   0.9040   0.0881
  -2.750   0.0220   0.03595   0.02696  -0.0647   0.8911   0.0849
  -2.500   0.0577   0.03385   0.02450  -0.0663   0.8785   0.0815
  -2.250   0.0943   0.03204   0.02222  -0.0676   0.8663   0.0785
  -2.000   0.1301   0.03053   0.02026  -0.0686   0.8543   0.0769
  -1.750   0.1610   0.02925   0.01876  -0.0691   0.8408   0.0783
  -1.500   0.1919   0.02817   0.01744  -0.0693   0.8275   0.0801
  -1.250   0.2229   0.02718   0.01617  -0.0694   0.8148   0.0802
  -1.000   0.2542   0.02627   0.01499  -0.0695   0.8030   0.0801
  -0.750   0.2853   0.02547   0.01398  -0.0694   0.7912   0.0803
  -0.500   0.3138   0.02486   0.01319  -0.0689   0.7785   0.0810
  -0.250   0.3436   0.02434   0.01250  -0.0687   0.7664   0.0824
   0.000   0.3728   0.02394   0.01193  -0.0683   0.7553   0.0864
   0.250   0.4002   0.02363   0.01148  -0.0677   0.7439   0.0899
   0.500   0.4254   0.02329   0.01111  -0.0670   0.7316   0.0929
   0.750   0.4514   0.02307   0.01081  -0.0664   0.7201   0.0965
   1.000   0.4784   0.02289   0.01049  -0.0657   0.7093   0.1015
   1.250   0.5038   0.02275   0.01031  -0.0650   0.6964   0.1088
   1.500   0.5289   0.02259   0.01018  -0.0643   0.6828   0.1267
   1.750   0.5688   0.02029   0.00995  -0.0662   0.6683   1.0000
   2.000   0.5931   0.02051   0.00985  -0.0650   0.6541   1.0000
   2.250   0.6172   0.02073   0.00985  -0.0639   0.6402   1.0000
   2.500   0.6415   0.02094   0.00990  -0.0629   0.6269   1.0000
   2.750   0.6661   0.02116   0.00999  -0.0619   0.6144   1.0000
   3.000   0.6908   0.02137   0.01009  -0.0609   0.6020   1.0000
   3.250   0.7146   0.02165   0.01032  -0.0600   0.5886   1.0000
   3.500   0.7385   0.02194   0.01057  -0.0591   0.5754   1.0000
   3.750   0.7626   0.02223   0.01083  -0.0581   0.5624   1.0000
   4.000   0.7868   0.02253   0.01108  -0.0572   0.5494   1.0000
   4.250   0.8112   0.02282   0.01135  -0.0563   0.5364   1.0000
   4.500   0.8357   0.02314   0.01163  -0.0554   0.5233   1.0000
   4.750   0.8588   0.02356   0.01208  -0.0544   0.5088   1.0000
   5.000   0.8818   0.02400   0.01256  -0.0535   0.4941   1.0000
   5.250   0.9046   0.02448   0.01311  -0.0525   0.4796   1.0000
   5.500   0.9273   0.02499   0.01369  -0.0516   0.4655   1.0000
   5.750   0.9499   0.02552   0.01429  -0.0507   0.4517   1.0000
   6.000   0.9725   0.02604   0.01491  -0.0497   0.4384   1.0000
   6.250   0.9945   0.02652   0.01545  -0.0487   0.4241   1.0000
   6.500   1.0159   0.02697   0.01597  -0.0475   0.4094   1.0000
   6.750   1.0372   0.02743   0.01649  -0.0464   0.3953   1.0000
   7.000   1.0577   0.02788   0.01704  -0.0452   0.3804   1.0000
   7.250   1.0775   0.02835   0.01758  -0.0439   0.3655   1.0000
   7.500   1.0963   0.02885   0.01816  -0.0425   0.3496   1.0000
   7.750   1.1150   0.02941   0.01880  -0.0411   0.3352   1.0000
   8.000   1.1329   0.03002   0.01953  -0.0397   0.3206   1.0000
   8.250   1.1484   0.03071   0.02032  -0.0381   0.3036   1.0000
   8.500   1.1626   0.03146   0.02119  -0.0365   0.2863   1.0000
   8.750   1.1749   0.03230   0.02214  -0.0346   0.2679   1.0000
   9.000   1.1828   0.03326   0.02310  -0.0324   0.2453   1.0000
   9.250   1.1890   0.03448   0.02447  -0.0303   0.2214   1.0000
   9.500   1.1925   0.03589   0.02596  -0.0280   0.1963   1.0000
   9.750   1.1917   0.03757   0.02774  -0.0255   0.1640   1.0000
  10.000   1.1863   0.03976   0.02980  -0.0233   0.1319   1.0000
  10.250   1.1783   0.04255   0.03238  -0.0216   0.1136   1.0000
  10.500   1.1703   0.04573   0.03544  -0.0207   0.1034   1.0000
  10.750   1.1636   0.04909   0.03876  -0.0203   0.0967   1.0000
  11.000   1.1571   0.05260   0.04223  -0.0201   0.0921   1.0000
  11.250   1.1540   0.05588   0.04562  -0.0199   0.0877   1.0000
  11.500   1.1500   0.05935   0.04916  -0.0200   0.0838   1.0000
  12.000   1.1468   0.06595   0.05593  -0.0200   0.0771   1.0000
  12.250   1.1482   0.06902   0.05916  -0.0200   0.0742   1.0000
  12.500   1.1509   0.07194   0.06219  -0.0197   0.0719   1.0000
  12.750   1.1546   0.07470   0.06501  -0.0194   0.0696   1.0000
  13.000   1.1593   0.07749   0.06788  -0.0191   0.0673   1.0000
  13.250   1.1596   0.08116   0.07185  -0.0196   0.0652   1.0000
  13.500   1.1584   0.08505   0.07600  -0.0204   0.0631   1.0000
  13.750   1.1580   0.08889   0.08003  -0.0211   0.0614   1.0000
  14.000   1.1582   0.09273   0.08404  -0.0218   0.0602   1.0000
  14.250   1.1606   0.09615   0.08755  -0.0222   0.0587   1.0000
  14.500   1.1568   0.10079   0.09234  -0.0237   0.0576   1.0000
  14.750   1.1427   0.10751   0.09933  -0.0269   0.0571   1.0000
  15.000   1.1257   0.11515   0.10723  -0.0310   0.0568   1.0000
  15.250   1.1062   0.12389   0.11620  -0.0360   0.0568   1.0000
  15.500   1.0839   0.13398   0.12647  -0.0419   0.0570   1.0000
  15.750   1.0600   0.14539   0.13797  -0.0487   0.0574   1.0000
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