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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 200,000
Max Cl/Cd: 70.32 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe585-il-200000.txt
Download as CSV file: xf-goe585-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3921   0.08673   0.08321  -0.0264   1.0000   0.0553
  -7.750  -0.3994   0.08423   0.08077  -0.0266   1.0000   0.0571
  -7.500  -0.4165   0.08138   0.07802  -0.0307   1.0000   0.0592
  -7.250  -0.4253   0.07722   0.07381  -0.0385   1.0000   0.0600
  -7.000  -0.4295   0.07229   0.06894  -0.0368   1.0000   0.0608
  -6.750  -0.4244   0.07096   0.06769  -0.0311   1.0000   0.0622
  -6.500  -0.4213   0.06909   0.06585  -0.0287   1.0000   0.0637
  -6.250  -0.4193   0.06664   0.06341  -0.0280   1.0000   0.0655
  -6.000  -0.4162   0.06360   0.06034  -0.0287   1.0000   0.0683
  -5.750  -0.4105   0.05617   0.05250  -0.0368   1.0000   0.0734
  -5.500  -0.4044   0.05386   0.05029  -0.0343   1.0000   0.0744
  -5.250  -0.3968   0.05210   0.04856  -0.0322   1.0000   0.0758
  -5.000  -0.3876   0.05032   0.04676  -0.0308   1.0000   0.0787
  -4.750  -0.3469   0.04408   0.04007  -0.0389   0.9953   0.0884
  -4.500  -0.3158   0.04167   0.03765  -0.0412   0.9910   0.0917
  -4.250  -0.2767   0.03722   0.03266  -0.0464   0.9858   0.1025
  -4.000  -0.2441   0.03506   0.03052  -0.0485   0.9816   0.1063
  -3.750  -0.2057   0.02341   0.01675  -0.0494   0.9775   0.0602
  -3.500  -0.1700   0.02108   0.01403  -0.0512   0.9736   0.0605
  -3.250  -0.1320   0.01919   0.01192  -0.0535   0.9709   0.0623
  -3.000  -0.1006   0.01807   0.01064  -0.0541   0.9639   0.0632
  -2.750  -0.0602   0.01708   0.00953  -0.0564   0.9595   0.0647
  -2.500  -0.0206   0.01620   0.00858  -0.0584   0.9521   0.0668
  -2.250   0.0256   0.01544   0.00775  -0.0616   0.9455   0.0714
  -2.000   0.0652   0.01444   0.00678  -0.0636   0.9380   0.0757
  -1.750   0.1068   0.01376   0.00614  -0.0660   0.9320   0.0832
  -1.500   0.1512   0.01295   0.00547  -0.0690   0.9288   0.1052
  -1.250   0.1816   0.01226   0.00507  -0.0693   0.9193   0.1731
  -1.000   0.2209   0.01152   0.00476  -0.0715   0.9143   0.2737
  -0.750   0.2477   0.01077   0.00459  -0.0712   0.9037   0.4329
  -0.500   0.3413   0.00917   0.00437  -0.0840   0.9059   1.0000
  -0.250   0.3755   0.00902   0.00409  -0.0848   0.8946   1.0000
   0.000   0.4068   0.00891   0.00386  -0.0849   0.8815   1.0000
   0.250   0.4341   0.00884   0.00369  -0.0843   0.8660   1.0000
   0.500   0.4598   0.00881   0.00357  -0.0833   0.8492   1.0000
   0.750   0.4849   0.00879   0.00346  -0.0822   0.8312   1.0000
   1.000   0.5102   0.00878   0.00335  -0.0812   0.8123   1.0000
   1.250   0.5357   0.00879   0.00325  -0.0801   0.7926   1.0000
   1.500   0.5596   0.00884   0.00320  -0.0789   0.7704   1.0000
   1.750   0.5843   0.00893   0.00315  -0.0777   0.7479   1.0000
   2.000   0.6077   0.00905   0.00315  -0.0764   0.7222   1.0000
   2.250   0.6306   0.00920   0.00319  -0.0749   0.6941   1.0000
   2.500   0.6528   0.00939   0.00323  -0.0734   0.6622   1.0000
   2.750   0.6744   0.00961   0.00329  -0.0717   0.6251   1.0000
   3.000   0.6948   0.00988   0.00336  -0.0699   0.5790   1.0000
   3.250   0.7141   0.01026   0.00348  -0.0679   0.5257   1.0000
   3.500   0.7330   0.01073   0.00365  -0.0660   0.4784   1.0000
   3.750   0.7533   0.01121   0.00390  -0.0644   0.4433   1.0000
   4.000   0.7744   0.01170   0.00419  -0.0630   0.4174   1.0000
   4.250   0.7967   0.01212   0.00452  -0.0619   0.3956   1.0000
   4.500   0.8192   0.01256   0.00485  -0.0609   0.3771   1.0000
   4.750   0.8420   0.01299   0.00519  -0.0599   0.3607   1.0000
   5.000   0.8652   0.01340   0.00555  -0.0589   0.3460   1.0000
   5.250   0.8887   0.01382   0.00595  -0.0581   0.3331   1.0000
   5.500   0.9121   0.01425   0.00634  -0.0572   0.3210   1.0000
   5.750   0.9351   0.01465   0.00671  -0.0563   0.3083   1.0000
   6.000   0.9578   0.01502   0.00706  -0.0554   0.2951   1.0000
   6.250   0.9805   0.01538   0.00740  -0.0544   0.2830   1.0000
   6.500   1.0038   0.01571   0.00781  -0.0536   0.2725   1.0000
   6.750   1.0268   0.01612   0.00824  -0.0527   0.2630   1.0000
   7.000   1.0495   0.01653   0.00865  -0.0518   0.2534   1.0000
   7.250   1.0721   0.01683   0.00908  -0.0508   0.2430   1.0000
   7.500   1.0938   0.01716   0.00945  -0.0497   0.2311   1.0000
   7.750   1.1145   0.01741   0.00975  -0.0486   0.2167   1.0000
   8.000   1.1352   0.01768   0.01009  -0.0474   0.2015   1.0000
   8.250   1.1557   0.01801   0.01048  -0.0462   0.1858   1.0000
   8.500   1.1752   0.01842   0.01089  -0.0449   0.1673   1.0000
   8.750   1.1944   0.01891   0.01137  -0.0435   0.1408   1.0000
   9.000   1.2100   0.01980   0.01210  -0.0418   0.1044   1.0000
   9.250   1.2194   0.02130   0.01336  -0.0392   0.0766   1.0000
   9.500   1.2275   0.02286   0.01488  -0.0364   0.0595   1.0000
   9.750   1.2335   0.02445   0.01647  -0.0333   0.0504   1.0000
  10.000   1.2414   0.02571   0.01778  -0.0304   0.0451   1.0000
  10.250   1.2432   0.02737   0.01946  -0.0268   0.0419   1.0000
  10.500   1.2525   0.02849   0.02071  -0.0242   0.0387   1.0000
  10.750   1.2592   0.02977   0.02204  -0.0217   0.0362   1.0000
  11.000   1.2612   0.03182   0.02409  -0.0189   0.0343   1.0000
  11.250   1.2693   0.03345   0.02586  -0.0167   0.0331   1.0000
  11.500   1.2776   0.03509   0.02765  -0.0146   0.0319   1.0000
  11.750   1.2852   0.03686   0.02955  -0.0127   0.0307   1.0000
  12.000   1.2922   0.03869   0.03150  -0.0110   0.0297   1.0000
  12.250   1.2974   0.04049   0.03337  -0.0094   0.0285   1.0000
  12.500   1.3036   0.04294   0.03586  -0.0080   0.0274   1.0000
  12.750   1.3067   0.04592   0.03904  -0.0066   0.0266   1.0000
  13.000   1.3061   0.04842   0.04179  -0.0051   0.0262   1.0000
  13.250   1.3036   0.05128   0.04488  -0.0039   0.0259   1.0000
  13.500   1.2987   0.05449   0.04834  -0.0030   0.0256   1.0000
  13.750   1.2917   0.05806   0.05215  -0.0025   0.0254   1.0000
  14.000   1.2815   0.06211   0.05643  -0.0026   0.0253   1.0000
  14.250   1.2691   0.06659   0.06116  -0.0033   0.0252   1.0000
  14.500   1.2542   0.07164   0.06644  -0.0047   0.0251   1.0000
  14.750   1.2373   0.07730   0.07233  -0.0068   0.0252   1.0000
  15.000   1.2187   0.08360   0.07884  -0.0098   0.0253   1.0000
  15.250   1.1977   0.09075   0.08621  -0.0138   0.0253   1.0000
  15.500   1.1758   0.09867   0.09433  -0.0185   0.0255   1.0000
  15.750   1.1528   0.10738   0.10322  -0.0240   0.0257   1.0000
  16.000   1.1291   0.11678   0.11279  -0.0301   0.0260   1.0000
  16.250   1.1039   0.12708   0.12323  -0.0368   0.0263   1.0000
  16.500   1.0776   0.13827   0.13452  -0.0438   0.0267   1.0000
  16.750   0.9669   0.18232   0.17868  -0.0687   0.0338   1.0000
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