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GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il)
Reynolds number: 50,000
Max Cl/Cd: 36.91 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe276-il-50000.txt
Download as CSV file: xf-goe276-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 276 (DAIMLER VII) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4103   0.10832   0.10158  -0.0186   1.0000   0.1333
  -7.750  -0.3939   0.10250   0.09577  -0.0161   1.0000   0.1394
  -7.500  -0.3950   0.10042   0.09377  -0.0175   1.0000   0.1464
  -7.250  -0.3942   0.09749   0.09093  -0.0197   1.0000   0.1508
  -7.000  -0.3879   0.09448   0.08796  -0.0195   1.0000   0.1615
  -6.500  -0.3817   0.08983   0.08345  -0.0268   1.0000   0.1789
  -6.250  -0.3726   0.08529   0.07897  -0.0214   1.0000   0.1913
  -6.000  -0.3657   0.08185   0.07559  -0.0204   1.0000   0.2018
  -5.750  -0.3595   0.07883   0.07264  -0.0209   1.0000   0.2152
  -5.500  -0.3526   0.07589   0.06975  -0.0208   1.0000   0.2313
  -5.250  -0.3444   0.07363   0.06750  -0.0247   1.0000   0.2544
  -4.750  -0.3338   0.06749   0.06151  -0.0176   1.0000   0.3034
  -4.500  -0.3290   0.06530   0.05937  -0.0162   1.0000   0.3446
  -4.250   0.0089   0.04114   0.03425  -0.0230   1.0000   1.0000
  -4.000   0.0196   0.03929   0.03247  -0.0237   1.0000   1.0000
  -3.750   0.0301   0.03753   0.03077  -0.0243   1.0000   1.0000
  -3.500   0.0400   0.03586   0.02917  -0.0248   1.0000   1.0000
  -3.250   0.0061   0.03639   0.02989  -0.0150   1.0000   0.9825
  -3.000  -0.0442   0.03729   0.03105  -0.0022   1.0000   0.9515
  -2.750  -0.0934   0.03791   0.03194   0.0096   1.0000   0.9267
  -2.500  -0.1379   0.03794   0.03223   0.0196   1.0000   0.9008
  -2.250  -0.1850   0.03788   0.03240   0.0302   1.0000   0.8848
  -2.000  -0.0227   0.03468   0.02667  -0.0554   1.0000   0.2773
  -1.750   0.0242   0.03271   0.02377  -0.0592   1.0000   0.2222
  -1.500   0.0568   0.03103   0.02171  -0.0602   1.0000   0.2036
  -1.250   0.0891   0.02972   0.01996  -0.0608   1.0000   0.1864
  -1.000   0.1196   0.02877   0.01860  -0.0611   1.0000   0.1748
  -0.750   0.1489   0.02793   0.01741  -0.0612   1.0000   0.1669
  -0.500   0.1762   0.02745   0.01665  -0.0611   1.0000   0.1624
  -0.250   0.2018   0.02693   0.01602  -0.0609   1.0000   0.1617
   0.000   0.2271   0.02671   0.01563  -0.0607   1.0000   0.1642
   0.250   0.2520   0.02646   0.01535  -0.0607   1.0000   0.1670
   0.500   0.2753   0.02654   0.01542  -0.0608   1.0000   0.1685
   0.750   0.2964   0.02697   0.01588  -0.0611   1.0000   0.1714
   1.000   0.3606   0.02698   0.01593  -0.0693   0.9825   0.1831
   1.250   0.4318   0.02441   0.01568  -0.0779   0.9572   0.8834
   1.500   0.5042   0.02426   0.01491  -0.0853   0.9202   1.0000
   1.750   0.5764   0.02375   0.01401  -0.0924   0.8894   1.0000
   2.000   0.6345   0.02317   0.01325  -0.0964   0.8586   1.0000
   2.250   0.6779   0.02286   0.01283  -0.0978   0.8263   1.0000
   2.500   0.7134   0.02273   0.01259  -0.0978   0.7957   1.0000
   2.750   0.7463   0.02266   0.01241  -0.0973   0.7683   1.0000
   3.000   0.7749   0.02280   0.01247  -0.0964   0.7417   1.0000
   3.250   0.8023   0.02305   0.01268  -0.0955   0.7165   1.0000
   3.500   0.8313   0.02324   0.01278  -0.0946   0.6946   1.0000
   3.750   0.8578   0.02367   0.01317  -0.0938   0.6720   1.0000
   4.000   0.8860   0.02406   0.01350  -0.0929   0.6520   1.0000
   4.250   0.9111   0.02477   0.01423  -0.0921   0.6304   1.0000
   4.500   0.9378   0.02541   0.01481  -0.0913   0.6104   1.0000
   4.750   0.9623   0.02621   0.01561  -0.0903   0.5886   1.0000
   5.000   0.9873   0.02688   0.01626  -0.0890   0.5660   1.0000
   5.250   1.0105   0.02774   0.01714  -0.0878   0.5431   1.0000
   5.500   1.0351   0.02858   0.01796  -0.0867   0.5222   1.0000
   5.750   1.0593   0.02962   0.01905  -0.0857   0.5032   1.0000
   6.000   1.0818   0.03088   0.02050  -0.0848   0.4841   1.0000
   6.250   1.1049   0.03215   0.02187  -0.0839   0.4657   1.0000
   6.500   1.1286   0.03342   0.02321  -0.0829   0.4476   1.0000
   6.750   1.1509   0.03487   0.02478  -0.0818   0.4297   1.0000
   7.000   1.1703   0.03667   0.02688  -0.0807   0.4125   1.0000
   7.250   1.1900   0.03859   0.02907  -0.0796   0.3970   1.0000
   7.500   1.2093   0.04057   0.03130  -0.0785   0.3826   1.0000
   7.750   1.2286   0.04247   0.03344  -0.0773   0.3688   1.0000
   8.000   1.2504   0.04420   0.03538  -0.0763   0.3562   1.0000
   8.250   1.2664   0.04580   0.03732  -0.0746   0.3405   1.0000
   8.500   1.2874   0.04347   0.03499  -0.0716   0.3074   1.0000
   8.750   1.3098   0.03911   0.03025  -0.0683   0.2671   1.0000
   9.000   1.3195   0.03821   0.02938  -0.0648   0.2311   1.0000
   9.250   1.3150   0.03893   0.02984  -0.0596   0.1769   1.0000
   9.500   1.3127   0.04163   0.03216  -0.0553   0.1372   1.0000
   9.750   1.3200   0.04445   0.03462  -0.0527   0.1171   1.0000
  10.000   1.3310   0.04740   0.03758  -0.0506   0.1039   1.0000
  10.250   1.3404   0.05075   0.04144  -0.0483   0.0967   1.0000
  10.500   1.3594   0.05423   0.04482  -0.0473   0.0907   1.0000
  10.750   1.3592   0.05802   0.04922  -0.0445   0.0880   1.0000
  11.000   1.3558   0.06185   0.05349  -0.0418   0.0856   1.0000
  11.250   1.3507   0.06548   0.05744  -0.0393   0.0833   1.0000
  11.500   1.3463   0.06882   0.06095  -0.0368   0.0812   1.0000
  11.750   1.3498   0.07283   0.06496  -0.0355   0.0788   1.0000
  12.000   1.3305   0.07716   0.06960  -0.0332   0.0788   1.0000
  12.250   1.3100   0.08201   0.07471  -0.0321   0.0789   1.0000
  12.500   1.2213   0.09441   0.08785  -0.0382   0.0873   1.0000
  12.750   1.1928   0.10319   0.09675  -0.0428   0.0891   1.0000
  13.000   1.1691   0.11221   0.10582  -0.0477   0.0903   1.0000
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