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GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 685 AIRFOIL (goe685-il)
Reynolds number: 50,000
Max Cl/Cd: 33.89 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe685-il-50000-n5.txt
Download as CSV file: xf-goe685-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 685 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3467   0.10210   0.09429  -0.0453   1.0000   0.0896
  -9.750  -0.3513   0.09865   0.09091  -0.0458   1.0000   0.0902
  -9.500  -0.3582   0.09508   0.08742  -0.0462   1.0000   0.0905
  -9.250  -0.3677   0.09143   0.08386  -0.0464   1.0000   0.0909
  -9.000  -0.3804   0.08779   0.08033  -0.0464   1.0000   0.0912
  -8.750  -0.3979   0.08411   0.07677  -0.0460   1.0000   0.0915
  -8.500  -0.4209   0.08058   0.07338  -0.0450   1.0000   0.0917
  -8.000  -0.4818   0.07166   0.06475  -0.0443   1.0000   0.0923
  -7.750  -0.5299   0.06040   0.05348  -0.0506   1.0000   0.0927
  -7.500  -0.5672   0.04717   0.03958  -0.0592   1.0000   0.0947
  -7.250  -0.5609   0.04471   0.03698  -0.0591   1.0000   0.0973
  -7.000  -0.5413   0.04373   0.03598  -0.0594   0.9973   0.1009
  -6.750  -0.5142   0.03836   0.02986  -0.0654   0.9898   0.1078
  -6.500  -0.4801   0.03804   0.02964  -0.0673   0.9828   0.1129
  -6.250  -0.4496   0.03590   0.02716  -0.0701   0.9749   0.1225
  -6.000  -0.4160   0.03453   0.02551  -0.0729   0.9678   0.1348
  -5.750  -0.3837   0.03387   0.02471  -0.0747   0.9595   0.1481
  -5.500  -0.3508   0.03368   0.02445  -0.0762   0.9515   0.1624
  -5.250  -0.3169   0.03362   0.02429  -0.0779   0.9431   0.1784
  -5.000  -0.2854   0.03400   0.02465  -0.0787   0.9341   0.1929
  -4.750  -0.2499   0.03426   0.02481  -0.0803   0.9257   0.2084
  -4.500  -0.2196   0.03446   0.02498  -0.0807   0.9156   0.2205
  -4.250  -0.1815   0.03416   0.02452  -0.0828   0.9075   0.2337
  -4.000  -0.1522   0.03350   0.02360  -0.0836   0.8962   0.2453
  -3.750  -0.1108   0.03300   0.02291  -0.0861   0.8890   0.2567
  -3.250  -0.0476   0.03181   0.02134  -0.0879   0.8686   0.2748
  -3.000  -0.0167   0.03130   0.02076  -0.0885   0.8584   0.2814
  -2.750   0.0144   0.03075   0.02002  -0.0892   0.8486   0.2900
  -2.500   0.0489   0.03014   0.01928  -0.0903   0.8400   0.2977
  -2.250   0.0763   0.02969   0.01872  -0.0902   0.8288   0.3046
  -2.000   0.1141   0.02905   0.01791  -0.0918   0.8215   0.3137
  -1.750   0.1396   0.02875   0.01755  -0.0913   0.8094   0.3213
  -1.500   0.1723   0.02825   0.01689  -0.0920   0.7999   0.3301
  -1.250   0.2038   0.02781   0.01642  -0.0923   0.7900   0.3381
  -1.000   0.2317   0.02752   0.01600  -0.0921   0.7787   0.3476
  -0.750   0.2681   0.02700   0.01543  -0.0930   0.7709   0.3580
  -0.500   0.2947   0.02679   0.01514  -0.0926   0.7584   0.3668
  -0.250   0.3261   0.02651   0.01477  -0.0928   0.7480   0.3777
   0.000   0.3599   0.02614   0.01438  -0.0933   0.7384   0.3888
   0.250   0.3876   0.02601   0.01419  -0.0931   0.7262   0.4001
   0.500   0.4214   0.02571   0.01382  -0.0936   0.7167   0.4137
   0.750   0.4498   0.02554   0.01369  -0.0934   0.7051   0.4260
   1.000   0.4773   0.02545   0.01363  -0.0931   0.6933   0.4395
   1.250   0.5111   0.02514   0.01334  -0.0935   0.6844   0.4560
   1.750   0.5624   0.02512   0.01349  -0.0924   0.6608   0.4912
   2.000   0.5915   0.02497   0.01346  -0.0923   0.6510   0.5156
   2.250   0.6144   0.02498   0.01372  -0.0914   0.6396   0.5484
   2.500   0.6425   0.02445   0.01363  -0.0906   0.6317   0.6294
   2.750   0.6765   0.02428   0.01395  -0.0917   0.6198   1.0000
   3.000   0.7047   0.02459   0.01409  -0.0916   0.6110   1.0000
   3.250   0.7296   0.02502   0.01442  -0.0910   0.6013   1.0000
   3.500   0.7550   0.02544   0.01476  -0.0906   0.5927   1.0000
   3.750   0.7802   0.02588   0.01512  -0.0900   0.5840   1.0000
   4.000   0.8049   0.02635   0.01555  -0.0894   0.5759   1.0000
   4.250   0.8291   0.02680   0.01597  -0.0888   0.5672   1.0000
   4.500   0.8529   0.02727   0.01641  -0.0880   0.5586   1.0000
   4.750   0.8774   0.02767   0.01680  -0.0873   0.5497   1.0000
   5.000   0.8991   0.02819   0.01732  -0.0862   0.5405   1.0000
   5.250   0.9252   0.02848   0.01758  -0.0856   0.5317   1.0000
   5.500   0.9441   0.02910   0.01826  -0.0842   0.5218   1.0000
   5.750   0.9730   0.02923   0.01834  -0.0838   0.5134   1.0000
   6.000   0.9886   0.02997   0.01916  -0.0821   0.5027   1.0000
   6.250   1.0157   0.03017   0.01935  -0.0815   0.4940   1.0000
   6.500   1.0326   0.03087   0.02014  -0.0799   0.4839   1.0000
   6.750   1.0566   0.03131   0.02061  -0.0791   0.4759   1.0000
   7.000   1.0738   0.03212   0.02153  -0.0776   0.4674   1.0000
   7.250   1.1010   0.03249   0.02195  -0.0772   0.4606   1.0000
   7.500   1.1127   0.03356   0.02318  -0.0752   0.4515   1.0000
   7.750   1.1419   0.03379   0.02343  -0.0749   0.4441   1.0000
   8.000   1.1500   0.03493   0.02476  -0.0725   0.4339   1.0000
   8.250   1.1721   0.03535   0.02525  -0.0713   0.4246   1.0000
   8.500   1.1875   0.03595   0.02595  -0.0694   0.4135   1.0000
   8.750   1.1965   0.03685   0.02698  -0.0669   0.4022   1.0000
   9.000   1.2149   0.03714   0.02731  -0.0652   0.3906   1.0000
   9.250   1.2239   0.03789   0.02818  -0.0626   0.3789   1.0000
   9.500   1.2232   0.03906   0.02949  -0.0592   0.3675   1.0000
   9.750   1.2323   0.03969   0.03019  -0.0566   0.3560   1.0000
  10.000   1.2366   0.04056   0.03113  -0.0538   0.3438   1.0000
  10.250   1.2285   0.04245   0.03318  -0.0506   0.3319   1.0000
  10.500   1.2262   0.04401   0.03484  -0.0481   0.3191   1.0000
  10.750   1.2239   0.04564   0.03657  -0.0458   0.3054   1.0000
  11.000   1.2209   0.04753   0.03853  -0.0440   0.2911   1.0000
  11.250   1.2178   0.04967   0.04075  -0.0424   0.2769   1.0000
  11.500   1.2148   0.05203   0.04318  -0.0412   0.2627   1.0000
  11.750   1.2097   0.05480   0.04604  -0.0404   0.2475   1.0000
  12.000   1.2031   0.05789   0.04918  -0.0398   0.2307   1.0000
  12.250   1.1985   0.06087   0.05215  -0.0393   0.2136   1.0000
  12.500   1.1946   0.06383   0.05503  -0.0389   0.1966   1.0000
  12.750   1.1895   0.06707   0.05816  -0.0386   0.1806   1.0000
  13.000   1.1824   0.07077   0.06180  -0.0387   0.1655   1.0000
  13.250   1.1745   0.07481   0.06580  -0.0390   0.1511   1.0000
  13.500   1.1672   0.07899   0.07000  -0.0395   0.1377   1.0000
  13.750   1.1615   0.08311   0.07416  -0.0402   0.1261   1.0000
  14.000   1.1573   0.08707   0.07809  -0.0408   0.1168   1.0000
  14.250   1.1545   0.09099   0.08207  -0.0416   0.1090   1.0000
  14.500   1.1526   0.09471   0.08574  -0.0423   0.1032   1.0000
  14.750   1.1520   0.09827   0.08929  -0.0431   0.0983   1.0000
  15.000   1.1535   0.10145   0.09239  -0.0436   0.0946   1.0000
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