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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 500,000
Max Cl/Cd: 73.11 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe100-il-500000-n5.txt
Download as CSV file: xf-goe100-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3777   0.09120   0.08908  -0.0214   1.0000   0.0064
  -7.500  -0.3811   0.08862   0.08655  -0.0209   1.0000   0.0066
  -7.250  -0.3889   0.08644   0.08443  -0.0196   1.0000   0.0066
  -7.000  -0.3854   0.08303   0.08105  -0.0218   0.9989   0.0067
  -6.750  -0.3579   0.07815   0.07615  -0.0305   0.9954   0.0074
  -6.500  -0.3384   0.07258   0.07056  -0.0373   0.9910   0.0071
  -6.250  -0.3146   0.06478   0.06270  -0.0462   0.9867   0.0042
  -6.000  -0.2887   0.05942   0.05728  -0.0528   0.9813   0.0041
  -5.750  -0.2572   0.05334   0.05110  -0.0602   0.9782   0.0040
  -5.500  -0.2282   0.04731   0.04495  -0.0658   0.9715   0.0040
  -5.250  -0.1943   0.04051   0.03794  -0.0717   0.9677   0.0041
  -4.750  -0.1314   0.02119   0.01746  -0.0786   0.9559   0.0047
  -4.500  -0.1034   0.01773   0.01342  -0.0791   0.9500   0.0046
  -4.250  -0.0736   0.01522   0.01040  -0.0797   0.9449   0.0047
  -4.000  -0.0435   0.01329   0.00807  -0.0801   0.9393   0.0048
  -3.750  -0.0142   0.01198   0.00648  -0.0804   0.9318   0.0050
  -3.500   0.0151   0.01110   0.00543  -0.0805   0.9242   0.0054
  -3.250   0.0439   0.01042   0.00460  -0.0806   0.9159   0.0060
  -3.000   0.0719   0.00990   0.00393  -0.0803   0.9047   0.0069
  -2.750   0.0991   0.00941   0.00326  -0.0800   0.8909   0.0087
  -2.500   0.1262   0.00898   0.00266  -0.0795   0.8766   0.0109
  -2.250   0.1535   0.00872   0.00226  -0.0792   0.8648   0.0144
  -2.000   0.1808   0.00851   0.00213  -0.0790   0.8550   0.0414
  -1.750   0.2081   0.00843   0.00200  -0.0788   0.8443   0.0525
  -1.500   0.2353   0.00836   0.00186  -0.0786   0.8304   0.0587
  -1.250   0.2622   0.00826   0.00170  -0.0783   0.8131   0.0639
  -1.000   0.2891   0.00821   0.00154  -0.0780   0.7942   0.0669
  -0.750   0.3161   0.00816   0.00142  -0.0777   0.7763   0.0746
  -0.500   0.3429   0.00804   0.00136  -0.0775   0.7551   0.1122
  -0.250   0.3692   0.00806   0.00130  -0.0771   0.7237   0.1413
   0.000   0.3943   0.00819   0.00126  -0.0765   0.6725   0.1597
   0.250   0.4184   0.00846   0.00127  -0.0757   0.6077   0.1747
   0.500   0.4426   0.00877   0.00133  -0.0751   0.5447   0.1946
   0.750   0.4677   0.00899   0.00141  -0.0747   0.4957   0.2201
   1.000   0.4929   0.00898   0.00153  -0.0745   0.4537   0.3410
   1.250   0.5096   0.00784   0.00167  -0.0725   0.4161   0.8609
   1.500   0.5423   0.00792   0.00174  -0.0734   0.3741   1.0000
   1.750   0.5680   0.00817   0.00183  -0.0731   0.3454   1.0000
   2.000   0.5940   0.00840   0.00194  -0.0729   0.3217   1.0000
   2.500   0.6463   0.00884   0.00218  -0.0724   0.2830   1.0000
   2.750   0.6710   0.00923   0.00235  -0.0720   0.2418   1.0000
   3.000   0.6963   0.00957   0.00253  -0.0717   0.2091   1.0000
   3.250   0.7215   0.00992   0.00273  -0.0714   0.1810   1.0000
   3.500   0.7461   0.01035   0.00295  -0.0710   0.1462   1.0000
   3.750   0.7648   0.01165   0.00360  -0.0697   0.0234   1.0000
   4.000   0.7906   0.01196   0.00399  -0.0693   0.0124   1.0000
   4.250   0.8165   0.01226   0.00437  -0.0690   0.0100   1.0000
   4.500   0.8421   0.01260   0.00479  -0.0686   0.0081   1.0000
   4.750   0.8663   0.01317   0.00550  -0.0679   0.0065   1.0000
   5.000   0.8910   0.01364   0.00608  -0.0673   0.0060   1.0000
   5.250   0.9147   0.01431   0.00685  -0.0666   0.0055   1.0000
   5.500   0.9384   0.01491   0.00750  -0.0659   0.0047   1.0000
   5.750   0.9604   0.01574   0.00839  -0.0650   0.0039   1.0000
   6.000   0.9820   0.01662   0.00937  -0.0639   0.0036   1.0000
   6.250   1.0020   0.01771   0.01054  -0.0624   0.0033   1.0000
   6.500   1.0209   0.01892   0.01186  -0.0608   0.0032   1.0000
   6.750   1.0396   0.02023   0.01322  -0.0592   0.0032   1.0000
   7.000   1.0588   0.02166   0.01471  -0.0577   0.0032   1.0000
   7.250   1.0790   0.02323   0.01632  -0.0563   0.0033   1.0000
   7.500   1.1004   0.02496   0.01811  -0.0551   0.0034   1.0000
   7.750   1.1222   0.02693   0.02016  -0.0541   0.0035   1.0000
   8.000   1.1438   0.02896   0.02232  -0.0530   0.0036   1.0000
   8.250   1.1633   0.03016   0.02373  -0.0515   0.0030   1.0000
   8.500   1.1809   0.03170   0.02536  -0.0505   0.0026   1.0000
   8.750   1.1955   0.03513   0.02892  -0.0493   0.0024   1.0000
   9.000   1.2101   0.03645   0.03060  -0.0469   0.0022   1.0000
   9.250   1.2214   0.03887   0.03331  -0.0444   0.0021   1.0000
   9.500   1.2292   0.04151   0.03625  -0.0417   0.0021   1.0000
   9.750   1.2332   0.04430   0.03933  -0.0387   0.0021   1.0000
  10.000   1.2336   0.04719   0.04246  -0.0356   0.0021   1.0000
  10.250   1.2298   0.05009   0.04561  -0.0323   0.0021   1.0000
  10.500   1.2193   0.05277   0.04849  -0.0282   0.0021   1.0000
  10.750   1.2065   0.05565   0.05155  -0.0247   0.0022   1.0000
  11.000   1.1921   0.05884   0.05492  -0.0219   0.0022   1.0000
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