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GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 363 AIRFOIL (goe363-il)
Reynolds number: 50,000
Max Cl/Cd: 32.68 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe363-il-50000.txt
Download as CSV file: xf-goe363-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 363 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2630   0.11394   0.10780  -0.0266   1.0000   0.1684
  -8.250  -0.2823   0.11429   0.10829  -0.0247   1.0000   0.1712
  -8.000  -0.3088   0.11538   0.10955  -0.0221   1.0000   0.1722
  -7.750  -0.2941   0.11001   0.10419  -0.0203   1.0000   0.1762
  -7.500  -0.2961   0.10786   0.10211  -0.0179   1.0000   0.1808
  -7.250  -0.3116   0.10719   0.10155  -0.0152   1.0000   0.1843
  -7.000  -0.3362   0.10746   0.10196  -0.0126   1.0000   0.1866
  -6.750  -0.3623   0.10821   0.10285  -0.0135   1.0000   0.1882
  -6.500  -0.3495   0.10295   0.09763  -0.0095   1.0000   0.1919
  -6.250  -0.3501   0.10055   0.09528  -0.0075   1.0000   0.1970
  -6.000  -0.3633   0.09961   0.09444  -0.0085   1.0000   0.2026
  -5.750  -0.3704   0.09742   0.09233  -0.0098   1.0000   0.2057
  -5.500  -0.3647   0.09403   0.08899  -0.0060   1.0000   0.2109
  -5.250  -0.3710   0.09329   0.08826  -0.0119   1.0000   0.2201
  -5.000  -0.3667   0.08921   0.08428  -0.0069   1.0000   0.2247
  -4.750  -0.3641   0.08768   0.08273  -0.0125   1.0000   0.2369
  -4.500  -0.3610   0.08413   0.07928  -0.0067   1.0000   0.2432
  -4.250  -0.3551   0.08158   0.07673  -0.0094   1.0000   0.2552
  -4.000  -0.3458   0.07921   0.07434  -0.0121   1.0000   0.2695
  -3.750  -0.3389   0.07660   0.07177  -0.0107   1.0000   0.2816
  -3.500  -0.3248   0.07420   0.06932  -0.0145   1.0000   0.3003
  -3.250  -0.3163   0.07145   0.06662  -0.0137   1.0000   0.3166
  -3.000  -0.3101   0.06888   0.06411  -0.0115   1.0000   0.3352
  -2.750  -0.3011   0.06669   0.06195  -0.0109   1.0000   0.3655
  -2.500  -0.2951   0.06453   0.05986  -0.0087   1.0000   0.3982
  -2.250  -0.2810   0.06214   0.05753  -0.0065   0.9956   0.4470
  -2.000  -0.0702   0.05151   0.04487  -0.0613   0.9805   0.2090
  -1.750   0.0159   0.04634   0.03847  -0.0741   0.9702   0.1704
  -1.500   0.0766   0.04409   0.03553  -0.0812   0.9569   0.1736
  -1.250   0.1351   0.04241   0.03350  -0.0872   0.9416   0.1800
  -1.000   0.1931   0.04099   0.03166  -0.0925   0.9241   0.1954
  -0.750   0.2439   0.03976   0.03011  -0.0962   0.9051   0.2231
  -0.500   0.2949   0.03846   0.02879  -0.0994   0.8871   0.2934
  -0.250   0.3428   0.03750   0.02800  -0.1023   0.8695   0.3919
   0.000   0.3901   0.03653   0.02720  -0.1048   0.8528   0.4587
   0.250   0.4334   0.03504   0.02651  -0.1064   0.8370   0.5743
   0.500   0.4732   0.03409   0.02573  -0.1064   0.8200   1.0000
   0.750   0.5188   0.03394   0.02509  -0.1080   0.8033   1.0000
   1.000   0.5629   0.03363   0.02446  -0.1092   0.7868   1.0000
   1.250   0.5909   0.03369   0.02432  -0.1084   0.7664   1.0000
   1.500   0.6267   0.03329   0.02374  -0.1081   0.7477   1.0000
   1.750   0.6649   0.03263   0.02291  -0.1078   0.7297   1.0000
   2.000   0.7052   0.03169   0.02182  -0.1075   0.7120   1.0000
   2.250   0.7467   0.03055   0.02052  -0.1072   0.6945   1.0000
   2.500   0.7740   0.03023   0.02010  -0.1056   0.6709   1.0000
   2.750   0.8125   0.02929   0.01900  -0.1051   0.6513   1.0000
   3.000   0.8468   0.02872   0.01825  -0.1043   0.6300   1.0000
   3.250   0.8773   0.02855   0.01792  -0.1033   0.6076   1.0000
   3.500   0.9117   0.02830   0.01744  -0.1028   0.5883   1.0000
   3.750   0.9380   0.02881   0.01779  -0.1020   0.5686   1.0000
   4.000   0.9637   0.02955   0.01841  -0.1013   0.5514   1.0000
   4.250   0.9899   0.03035   0.01912  -0.1008   0.5364   1.0000
   4.500   1.0171   0.03112   0.01977  -0.1003   0.5229   1.0000
   4.750   1.0421   0.03204   0.02062  -0.0998   0.5102   1.0000
   5.000   1.0600   0.03347   0.02215  -0.0987   0.4980   1.0000
   5.250   1.0808   0.03478   0.02348  -0.0980   0.4877   1.0000
   5.500   1.1114   0.03535   0.02390  -0.0978   0.4774   1.0000
   5.750   1.1250   0.03683   0.02550  -0.0963   0.4653   1.0000
   6.000   1.1423   0.03800   0.02675  -0.0949   0.4533   1.0000
   6.250   1.1648   0.03878   0.02750  -0.0939   0.4418   1.0000
   6.500   1.1957   0.03897   0.02753  -0.0936   0.4306   1.0000
   6.750   1.2034   0.04086   0.02966  -0.0916   0.4202   1.0000
   7.000   1.2215   0.04221   0.03110  -0.0905   0.4113   1.0000
   7.250   1.2445   0.04316   0.03207  -0.0897   0.4022   1.0000
   7.500   1.2484   0.04557   0.03471  -0.0876   0.3936   1.0000
   7.750   1.2836   0.04585   0.03490  -0.0878   0.3853   1.0000
   8.000   1.2675   0.04982   0.03927  -0.0843   0.3776   1.0000
   8.250   1.3113   0.04967   0.03898  -0.0851   0.3698   1.0000
   8.500   1.2654   0.05597   0.04577  -0.0799   0.3634   1.0000
   8.750   1.3001   0.05646   0.04625  -0.0800   0.3560   1.0000
   9.000   1.2298   0.06513   0.05522  -0.0747   0.3519   1.0000
   9.250   0.7927   0.13328   0.12349  -0.1038   0.4824   1.0000
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