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GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 645 AIRFOIL (goe645-il)
Reynolds number: 100,000
Max Cl/Cd: 43.66 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe645-il-100000.txt
Download as CSV file: xf-goe645-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 645 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2639   0.10580   0.10113  -0.0371   1.0000   0.1611
  -9.250  -0.3114   0.10551   0.10107  -0.0374   1.0000   0.1620
  -8.500  -0.5307   0.05604   0.05132  -0.0659   0.9829   0.0937
  -8.250  -0.5287   0.04667   0.04119  -0.0739   0.9704   0.0937
  -8.000  -0.5106   0.04137   0.03533  -0.0775   0.9595   0.0948
  -7.750  -0.4706   0.03973   0.03377  -0.0806   0.9522   0.0979
  -7.500  -0.4412   0.03697   0.03064  -0.0832   0.9420   0.1015
  -7.250  -0.4156   0.03387   0.02685  -0.0849   0.9314   0.1049
  -7.000  -0.3756   0.03154   0.02434  -0.0880   0.9245   0.1091
  -6.750  -0.3441   0.03026   0.02290  -0.0891   0.9138   0.1150
  -6.500  -0.3001   0.02826   0.02069  -0.0923   0.9077   0.1228
  -6.250  -0.2682   0.02702   0.01918  -0.0932   0.8971   0.1320
  -6.000  -0.2225   0.02558   0.01772  -0.0963   0.8910   0.1481
  -5.750  -0.1905   0.02494   0.01726  -0.0968   0.8800   0.1658
  -5.500  -0.1466   0.02462   0.01691  -0.0991   0.8728   0.1911
  -5.250  -0.1168   0.02461   0.01684  -0.0990   0.8604   0.2082
  -5.000  -0.0730   0.02440   0.01655  -0.1011   0.8534   0.2251
  -4.750  -0.0458   0.02451   0.01680  -0.1004   0.8398   0.2357
  -4.500  -0.0156   0.02440   0.01663  -0.1003   0.8280   0.2483
  -4.250   0.0195   0.02435   0.01652  -0.1009   0.8182   0.2640
  -4.000   0.0439   0.02430   0.01628  -0.0999   0.8044   0.2775
  -3.750   0.0720   0.02398   0.01603  -0.0993   0.7924   0.2864
  -3.500   0.1027   0.02335   0.01517  -0.0993   0.7820   0.2983
  -3.250   0.1264   0.02313   0.01489  -0.0982   0.7684   0.3099
  -3.000   0.1529   0.02278   0.01447  -0.0975   0.7569   0.3217
  -2.750   0.1814   0.02238   0.01391  -0.0972   0.7464   0.3359
  -2.500   0.2049   0.02226   0.01365  -0.0961   0.7336   0.3500
  -2.250   0.2327   0.02198   0.01336  -0.0956   0.7237   0.3626
  -2.000   0.2578   0.02180   0.01314  -0.0948   0.7122   0.3754
  -1.750   0.2825   0.02171   0.01295  -0.0939   0.7013   0.3887
  -1.500   0.3109   0.02152   0.01265  -0.0935   0.6921   0.4021
  -1.250   0.3339   0.02145   0.01263  -0.0925   0.6808   0.4130
  -1.000   0.3639   0.02123   0.01226  -0.0924   0.6728   0.4258
  -0.750   0.3860   0.02128   0.01232  -0.0913   0.6614   0.4383
  -0.500   0.4149   0.02109   0.01209  -0.0910   0.6535   0.4539
  -0.250   0.4373   0.02108   0.01215  -0.0898   0.6423   0.4694
   0.000   0.4639   0.02095   0.01199  -0.0892   0.6331   0.4856
   0.250   0.4899   0.02080   0.01183  -0.0885   0.6229   0.5012
   0.500   0.5152   0.02073   0.01178  -0.0878   0.6131   0.5174
   0.750   0.5433   0.02054   0.01158  -0.0874   0.6043   0.5370
   1.000   0.5679   0.02053   0.01166  -0.0866   0.5949   0.5598
   1.250   0.5970   0.02030   0.01151  -0.0865   0.5869   0.5936
   1.750   0.6992   0.01933   0.01132  -0.0946   0.5679   1.0000
   2.000   0.7201   0.01974   0.01163  -0.0934   0.5584   1.0000
   2.250   0.7482   0.01992   0.01157  -0.0931   0.5510   1.0000
   2.500   0.7688   0.02035   0.01195  -0.0918   0.5419   1.0000
   2.750   0.7957   0.02056   0.01199  -0.0914   0.5343   1.0000
   3.000   0.8171   0.02101   0.01240  -0.0902   0.5257   1.0000
   3.250   0.8429   0.02124   0.01249  -0.0896   0.5175   1.0000
   3.500   0.8648   0.02166   0.01287  -0.0884   0.5087   1.0000
   3.750   0.8900   0.02190   0.01299  -0.0877   0.5002   1.0000
   4.000   0.9118   0.02232   0.01337  -0.0866   0.4913   1.0000
   4.250   0.9370   0.02255   0.01350  -0.0859   0.4827   1.0000
   4.500   0.9582   0.02299   0.01391  -0.0847   0.4738   1.0000
   4.750   0.9830   0.02324   0.01407  -0.0839   0.4654   1.0000
   5.000   1.0044   0.02372   0.01453  -0.0828   0.4571   1.0000
   5.250   1.0276   0.02405   0.01482  -0.0819   0.4490   1.0000
   5.500   1.0514   0.02450   0.01521  -0.0811   0.4418   1.0000
   5.750   1.0708   0.02498   0.01573  -0.0797   0.4336   1.0000
   6.000   1.1016   0.02523   0.01578  -0.0800   0.4276   1.0000
   6.250   1.1138   0.02597   0.01671  -0.0777   0.4193   1.0000
   6.500   1.1398   0.02632   0.01698  -0.0773   0.4133   1.0000
   6.750   1.1607   0.02698   0.01767  -0.0762   0.4074   1.0000
   7.000   1.1773   0.02770   0.01850  -0.0746   0.4009   1.0000
   7.250   1.2042   0.02809   0.01881  -0.0744   0.3960   1.0000
   7.500   1.2234   0.02884   0.01963  -0.0732   0.3907   1.0000
   7.750   1.2373   0.02964   0.02055  -0.0713   0.3845   1.0000
   8.000   1.2636   0.02997   0.02083  -0.0710   0.3795   1.0000
   8.250   1.2846   0.03064   0.02153  -0.0701   0.3746   1.0000
   8.500   1.2935   0.03163   0.02271  -0.0676   0.3688   1.0000
   8.750   1.3159   0.03213   0.02322  -0.0668   0.3642   1.0000
   9.000   1.3506   0.03240   0.02335  -0.0678   0.3603   1.0000
   9.250   1.3468   0.03384   0.02510  -0.0637   0.3549   1.0000
   9.500   1.3620   0.03444   0.02578  -0.0620   0.3494   1.0000
   9.750   1.3970   0.03444   0.02565  -0.0629   0.3448   1.0000
  10.000   1.3974   0.03581   0.02725  -0.0595   0.3401   1.0000
  10.250   1.4005   0.03695   0.02855  -0.0565   0.3349   1.0000
  10.500   1.4300   0.03700   0.02855  -0.0566   0.3300   1.0000
  10.750   1.4430   0.03784   0.02946  -0.0548   0.3251   1.0000
  11.000   1.4282   0.03945   0.03129  -0.0496   0.3201   1.0000
  11.250   1.4544   0.03947   0.03129  -0.0492   0.3145   1.0000
  11.500   1.4694   0.04011   0.03195  -0.0477   0.3091   1.0000
  11.750   1.4433   0.04228   0.03435  -0.0420   0.3041   1.0000
  12.000   1.4827   0.04167   0.03364  -0.0428   0.2977   1.0000
  12.250   1.4725   0.04345   0.03557  -0.0392   0.2922   1.0000
  12.500   1.4491   0.04602   0.03833  -0.0352   0.2865   1.0000
  12.750   1.5112   0.04433   0.03642  -0.0373   0.2789   1.0000
  13.000   1.4501   0.04924   0.04168  -0.0315   0.2740   1.0000
  13.250   1.4753   0.04929   0.04169  -0.0310   0.2672   1.0000
  13.500   1.4743   0.05143   0.04389  -0.0294   0.2614   1.0000
  13.750   1.3577   0.06368   0.05653  -0.0272   0.2557   1.0000
  14.000   1.4793   0.05528   0.04786  -0.0271   0.2503   1.0000
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