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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 100,000
Max Cl/Cd: 52.2 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe235-il-100000.txt
Download as CSV file: xf-goe235-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 235 (SCHTTE-LANZ) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4287   0.10099   0.09585  -0.0024   1.0000   0.0643
  -7.750  -0.4220   0.09800   0.09290  -0.0040   1.0000   0.0658
  -7.500  -0.4163   0.09515   0.09008  -0.0062   1.0000   0.0675
  -7.250  -0.4086   0.09247   0.08744  -0.0116   1.0000   0.0695
  -7.000  -0.3896   0.09114   0.08598  -0.0297   1.0000   0.0710
  -6.750  -0.3849   0.08518   0.08018  -0.0227   1.0000   0.0720
  -6.500  -0.3748   0.08160   0.07665  -0.0200   1.0000   0.0737
  -6.250  -0.3620   0.07844   0.07352  -0.0211   1.0000   0.0760
  -6.000  -0.3469   0.07528   0.07036  -0.0242   1.0000   0.0788
  -5.750  -0.3094   0.07416   0.06883  -0.0407   1.0000   0.0837
  -5.500  -0.3045   0.06858   0.06348  -0.0375   1.0000   0.0847
  -5.250  -0.2962   0.06525   0.06026  -0.0351   1.0000   0.0863
  -5.000  -0.2849   0.06259   0.05765  -0.0345   1.0000   0.0888
  -4.750  -0.2712   0.06014   0.05519  -0.0354   1.0000   0.0927
  -4.500  -0.2450   0.05794   0.05268  -0.0416   1.0000   0.0989
  -4.250  -0.2419   0.05496   0.04987  -0.0387   1.0000   0.1006
  -4.000  -0.2354   0.05293   0.04789  -0.0367   1.0000   0.1038
  -3.750  -0.2106   0.05148   0.04609  -0.0405   1.0000   0.1143
  -3.500  -0.2055   0.04867   0.04346  -0.0382   1.0000   0.1167
  -3.250  -0.1941   0.04686   0.04169  -0.0373   1.0000   0.1220
  -3.000  -0.1731   0.04489   0.03953  -0.0392   1.0000   0.1318
  -2.750  -0.1607   0.04311   0.03779  -0.0383   1.0000   0.1377
  -2.500  -0.1298   0.04086   0.03544  -0.0414   0.9971   0.1514
  -2.250  -0.0822   0.03882   0.03316  -0.0475   0.9904   0.1798
  -2.000  -0.0414   0.03611   0.03053  -0.0516   0.9839   0.2033
  -0.500   0.2886   0.02297   0.01520  -0.0805   0.9263   0.1426
  -0.250   0.3266   0.02185   0.01375  -0.0810   0.9133   0.1276
   0.000   0.3612   0.02047   0.01222  -0.0812   0.9001   0.1179
   0.250   0.3939   0.01983   0.01137  -0.0806   0.8862   0.1118
   0.500   0.4235   0.01886   0.01038  -0.0797   0.8720   0.1094
   0.750   0.4510   0.01814   0.00963  -0.0783   0.8571   0.1084
   1.000   0.4768   0.01762   0.00908  -0.0766   0.8411   0.1112
   1.250   0.5017   0.01717   0.00862  -0.0748   0.8250   0.1132
   1.500   0.5256   0.01659   0.00812  -0.0729   0.8094   0.1152
   1.750   0.5500   0.01622   0.00778  -0.0713   0.7926   0.1195
   2.000   0.5750   0.01598   0.00750  -0.0697   0.7740   0.1283
   2.500   0.6233   0.01348   0.00694  -0.0661   0.7325   1.0000
   2.750   0.6481   0.01342   0.00664  -0.0642   0.7035   1.0000
   3.000   0.6717   0.01334   0.00628  -0.0620   0.6646   1.0000
   3.250   0.6944   0.01344   0.00603  -0.0597   0.6100   1.0000
   3.500   0.7167   0.01373   0.00595  -0.0579   0.5195   1.0000
   3.750   0.7372   0.01454   0.00596  -0.0561   0.4206   1.0000
   4.000   0.7605   0.01539   0.00638  -0.0553   0.3740   1.0000
   4.250   0.7852   0.01604   0.00680  -0.0547   0.3477   1.0000
   4.500   0.8104   0.01658   0.00720  -0.0542   0.3256   1.0000
   4.750   0.8357   0.01708   0.00760  -0.0537   0.3079   1.0000
   5.000   0.8610   0.01758   0.00802  -0.0532   0.2936   1.0000
   5.250   0.8860   0.01806   0.00846  -0.0528   0.2772   1.0000
   5.500   0.9105   0.01853   0.00889  -0.0523   0.2583   1.0000
   5.750   0.9347   0.01902   0.00934  -0.0517   0.2379   1.0000
   6.000   0.9591   0.01944   0.00978  -0.0512   0.2105   1.0000
   6.250   0.9837   0.01990   0.01022  -0.0507   0.1750   1.0000
   6.500   1.0087   0.02046   0.01067  -0.0500   0.1254   1.0000
   6.750   1.0305   0.02151   0.01134  -0.0492   0.0996   1.0000
   7.000   1.0514   0.02268   0.01239  -0.0482   0.0921   1.0000
   7.250   1.0724   0.02380   0.01355  -0.0472   0.0872   1.0000
   7.500   1.0915   0.02517   0.01488  -0.0460   0.0832   1.0000
   7.750   1.1112   0.02656   0.01626  -0.0448   0.0809   1.0000
   8.000   1.1327   0.02782   0.01761  -0.0437   0.0794   1.0000
   8.250   1.1547   0.02920   0.01906  -0.0427   0.0781   1.0000
   8.500   1.1774   0.03072   0.02065  -0.0418   0.0769   1.0000
   8.750   1.2001   0.03235   0.02237  -0.0409   0.0753   1.0000
   9.000   1.2227   0.03418   0.02426  -0.0402   0.0734   1.0000
   9.250   1.2458   0.03630   0.02645  -0.0396   0.0722   1.0000
   9.500   1.2684   0.03865   0.02897  -0.0389   0.0717   1.0000
   9.750   1.2891   0.04118   0.03175  -0.0380   0.0716   1.0000
  10.000   1.3074   0.04399   0.03486  -0.0370   0.0714   1.0000
  10.250   1.3226   0.04741   0.03860  -0.0359   0.0709   1.0000
  10.500   1.3332   0.05142   0.04296  -0.0347   0.0704   1.0000
  10.750   1.3405   0.05489   0.04684  -0.0331   0.0705   1.0000
  11.000   1.3433   0.05755   0.04998  -0.0309   0.0712   1.0000
  11.250   1.3295   0.06135   0.05446  -0.0280   0.0726   1.0000
  11.500   1.2899   0.06683   0.06060  -0.0247   0.0743   1.0000
  11.750   1.2508   0.07251   0.06665  -0.0234   0.0755   1.0000
  12.000   1.2091   0.07984   0.07427  -0.0255   0.0766   1.0000
  12.250   1.1603   0.09024   0.08488  -0.0318   0.0779   1.0000
  12.500   1.1130   0.10365   0.09842  -0.0408   0.0799   1.0000
  12.750   1.1009   0.11128   0.10606  -0.0437   0.0813   1.0000
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