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GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 593 AIRFOIL (goe593-il)
Reynolds number: 100,000
Max Cl/Cd: 53.2 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe593-il-100000-n5.txt
Download as CSV file: xf-goe593-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 593 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3720   0.09423   0.08935  -0.0413   1.0000   0.0407
  -9.000  -0.3847   0.09121   0.08642  -0.0405   1.0000   0.0409
  -8.750  -0.4000   0.08839   0.08370  -0.0393   1.0000   0.0409
  -8.500  -0.4194   0.08571   0.08112  -0.0378   1.0000   0.0408
  -8.250  -0.4219   0.07960   0.07503  -0.0446   0.9929   0.0407
  -8.000  -0.4190   0.07091   0.06628  -0.0552   0.9828   0.0404
  -7.750  -0.4188   0.06088   0.05602  -0.0646   0.9719   0.0403
  -7.500  -0.4148   0.05218   0.04693  -0.0707   0.9629   0.0413
  -7.250  -0.4123   0.04457   0.03870  -0.0734   0.9529   0.0429
  -7.000  -0.4053   0.03856   0.03183  -0.0739   0.9438   0.0443
  -6.750  -0.3829   0.03515   0.02793  -0.0750   0.9386   0.0456
  -6.500  -0.3596   0.03410   0.02682  -0.0750   0.9319   0.0475
  -6.250  -0.3341   0.03223   0.02464  -0.0755   0.9260   0.0497
  -6.000  -0.3043   0.02977   0.02165  -0.0767   0.9224   0.0516
  -5.750  -0.2837   0.02815   0.01951  -0.0756   0.9144   0.0538
  -5.500  -0.2535   0.02682   0.01811  -0.0765   0.9098   0.0559
  -5.250  -0.2191   0.02560   0.01672  -0.0779   0.9068   0.0582
  -5.000  -0.1966   0.02466   0.01559  -0.0769   0.8988   0.0602
  -4.750  -0.1644   0.02367   0.01434  -0.0777   0.8942   0.0636
  -4.500  -0.1291   0.02267   0.01330  -0.0792   0.8912   0.0667
  -4.250  -0.1054   0.02205   0.01263  -0.0784   0.8834   0.0693
  -4.000  -0.0735   0.02132   0.01181  -0.0791   0.8783   0.0733
  -3.750  -0.0372   0.02062   0.01108  -0.0807   0.8750   0.0792
  -3.500  -0.0141   0.02023   0.01065  -0.0797   0.8667   0.0855
  -3.250   0.0178   0.01963   0.01006  -0.0804   0.8614   0.0941
  -3.000   0.0538   0.01903   0.00948  -0.0819   0.8578   0.1096
  -2.750   0.0741   0.01875   0.00922  -0.0803   0.8481   0.1264
  -2.500   0.1083   0.01828   0.00876  -0.0814   0.8433   0.1514
  -2.250   0.1324   0.01795   0.00853  -0.0807   0.8349   0.1756
  -2.000   0.1633   0.01751   0.00822  -0.0812   0.8285   0.2133
  -1.750   0.1907   0.01706   0.00800  -0.0811   0.8209   0.2720
  -1.500   0.2186   0.01636   0.00775  -0.0811   0.8130   0.3788
  -1.250   0.2426   0.01546   0.00766  -0.0800   0.8049   0.6031
  -1.000   0.3105   0.01477   0.00764  -0.0864   0.7987   0.8807
  -0.750   0.3869   0.01458   0.00727  -0.0956   0.7915   0.9620
  -0.500   0.4467   0.01450   0.00701  -0.1019   0.7815   0.9979
  -0.250   0.4731   0.01449   0.00685  -0.1016   0.7702   1.0000
   0.000   0.4995   0.01444   0.00666  -0.1011   0.7599   1.0000
   0.250   0.5233   0.01445   0.00654  -0.1001   0.7485   1.0000
   0.500   0.5452   0.01450   0.00648  -0.0988   0.7364   1.0000
   0.750   0.5692   0.01453   0.00640  -0.0979   0.7248   1.0000
   1.000   0.5946   0.01455   0.00630  -0.0972   0.7133   1.0000
   1.250   0.6173   0.01463   0.00628  -0.0959   0.7007   1.0000
   1.500   0.6389   0.01472   0.00629  -0.0945   0.6875   1.0000
   1.750   0.6613   0.01482   0.00631  -0.0933   0.6743   1.0000
   2.000   0.6841   0.01493   0.00634  -0.0921   0.6613   1.0000
   2.250   0.7069   0.01504   0.00636  -0.0909   0.6478   1.0000
   2.500   0.7292   0.01517   0.00640  -0.0896   0.6336   1.0000
   2.750   0.7506   0.01532   0.00649  -0.0882   0.6190   1.0000
   3.000   0.7713   0.01548   0.00659  -0.0866   0.6034   1.0000
   3.250   0.7918   0.01566   0.00671  -0.0850   0.5876   1.0000
   3.500   0.8122   0.01585   0.00685  -0.0834   0.5712   1.0000
   3.750   0.8321   0.01606   0.00699  -0.0818   0.5539   1.0000
   4.000   0.8514   0.01629   0.00717  -0.0800   0.5356   1.0000
   4.250   0.8706   0.01654   0.00736  -0.0782   0.5169   1.0000
   4.500   0.8899   0.01681   0.00756  -0.0765   0.4983   1.0000
   4.750   0.9092   0.01712   0.00778  -0.0748   0.4808   1.0000
   5.000   0.9283   0.01745   0.00803  -0.0731   0.4641   1.0000
   5.250   0.9472   0.01781   0.00833  -0.0714   0.4479   1.0000
   5.500   0.9661   0.01820   0.00865  -0.0698   0.4328   1.0000
   5.750   0.9853   0.01860   0.00901  -0.0682   0.4191   1.0000
   6.000   1.0047   0.01902   0.00940  -0.0667   0.4070   1.0000
   6.250   1.0246   0.01947   0.00979  -0.0653   0.3964   1.0000
   6.500   1.0441   0.01991   0.01025  -0.0639   0.3856   1.0000
   6.750   1.0640   0.02037   0.01070  -0.0626   0.3761   1.0000
   7.000   1.0838   0.02085   0.01118  -0.0613   0.3670   1.0000
   7.250   1.1039   0.02133   0.01171  -0.0601   0.3586   1.0000
   7.500   1.1240   0.02184   0.01221  -0.0588   0.3508   1.0000
   7.750   1.1421   0.02234   0.01279  -0.0573   0.3416   1.0000
   8.000   1.1597   0.02285   0.01328  -0.0557   0.3325   1.0000
   8.250   1.1745   0.02334   0.01385  -0.0536   0.3225   1.0000
   8.500   1.1887   0.02385   0.01439  -0.0514   0.3131   1.0000
   8.750   1.2016   0.02437   0.01493  -0.0490   0.3035   1.0000
   9.000   1.2130   0.02490   0.01556  -0.0465   0.2931   1.0000
   9.250   1.2242   0.02547   0.01615  -0.0440   0.2833   1.0000
   9.500   1.2358   0.02606   0.01682  -0.0416   0.2741   1.0000
   9.750   1.2487   0.02668   0.01755  -0.0396   0.2662   1.0000
  10.000   1.2602   0.02734   0.01831  -0.0374   0.2580   1.0000
  10.250   1.2715   0.02803   0.01913  -0.0353   0.2495   1.0000
  10.500   1.2804   0.02881   0.01996  -0.0329   0.2407   1.0000
  10.750   1.2890   0.02963   0.02094  -0.0307   0.2303   1.0000
  11.000   1.2961   0.03056   0.02197  -0.0283   0.2199   1.0000
  11.250   1.3010   0.03162   0.02310  -0.0260   0.2087   1.0000
  11.500   1.3054   0.03281   0.02441  -0.0237   0.1958   1.0000
  11.750   1.3077   0.03420   0.02588  -0.0215   0.1806   1.0000
  12.000   1.3090   0.03579   0.02753  -0.0194   0.1625   1.0000
  12.250   1.3062   0.03777   0.02949  -0.0173   0.1445   1.0000
  12.500   1.3013   0.04008   0.03176  -0.0154   0.1300   1.0000
  12.750   1.2960   0.04260   0.03427  -0.0138   0.1190   1.0000
  13.000   1.2900   0.04534   0.03702  -0.0124   0.1111   1.0000
  13.250   1.2838   0.04826   0.03998  -0.0113   0.1043   1.0000
  13.500   1.2770   0.05138   0.04316  -0.0105   0.0987   1.0000
  13.750   1.2708   0.05459   0.04646  -0.0100   0.0934   1.0000
  14.000   1.2612   0.05831   0.05021  -0.0098   0.0894   1.0000
  14.250   1.2565   0.06166   0.05368  -0.0098   0.0851   1.0000
  14.500   1.2492   0.06546   0.05759  -0.0101   0.0811   1.0000
  14.750   1.2401   0.06957   0.06174  -0.0106   0.0781   1.0000
  15.000   1.2345   0.07340   0.06568  -0.0111   0.0749   1.0000
  15.250   1.2290   0.07736   0.06979  -0.0119   0.0716   1.0000
  15.500   1.2224   0.08154   0.07406  -0.0129   0.0689   1.0000
  15.750   1.2161   0.08559   0.07812  -0.0138   0.0663   1.0000
  16.000   1.2120   0.08963   0.08231  -0.0149   0.0636   1.0000
  16.250   1.2070   0.09389   0.08673  -0.0162   0.0607   1.0000
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