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GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il)
Reynolds number: 50,000
Max Cl/Cd: 22.41 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe290-il-50000-n5.txt
Download as CSV file: xf-goe290-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 290 (MVA 290) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3522   0.10328   0.09561  -0.0472   1.0000   0.0949
 -10.500  -0.3613   0.09797   0.09037  -0.0495   1.0000   0.0947
 -10.250  -0.3753   0.09194   0.08442  -0.0522   1.0000   0.0943
 -10.000  -0.4053   0.08332   0.07587  -0.0567   1.0000   0.0936
  -9.750  -0.4987   0.07016   0.06270  -0.0639   1.0000   0.0915
  -9.500  -0.5639   0.06494   0.05739  -0.0610   1.0000   0.0906
  -9.250  -0.5990   0.06156   0.05388  -0.0577   1.0000   0.0904
  -9.000  -0.5982   0.05761   0.04967  -0.0593   0.9911   0.0911
  -8.750  -0.5769   0.05374   0.04548  -0.0632   0.9767   0.0928
  -8.500  -0.5550   0.05007   0.04140  -0.0665   0.9617   0.0951
  -8.250  -0.5325   0.04651   0.03729  -0.0693   0.9463   0.0974
  -7.750  -0.4738   0.04169   0.03194  -0.0733   0.9151   0.1016
  -7.500  -0.4441   0.03995   0.03004  -0.0747   0.8983   0.1047
  -7.250  -0.4149   0.03811   0.02786  -0.0757   0.8816   0.1084
  -7.000  -0.3841   0.03640   0.02590  -0.0768   0.8658   0.1116
  -6.750  -0.3523   0.03509   0.02455  -0.0778   0.8506   0.1154
  -6.500  -0.3209   0.03380   0.02299  -0.0785   0.8362   0.1204
  -6.250  -0.2911   0.03260   0.02164  -0.0788   0.8215   0.1250
  -6.000  -0.2639   0.03168   0.02065  -0.0788   0.8061   0.1304
  -5.750  -0.2367   0.03083   0.01951  -0.0786   0.7916   0.1368
  -5.500  -0.2104   0.02995   0.01866  -0.0783   0.7786   0.1432
  -5.250  -0.1846   0.02925   0.01776  -0.0778   0.7654   0.1518
  -5.000  -0.1610   0.02853   0.01709  -0.0773   0.7527   0.1605
  -4.750  -0.1351   0.02780   0.01630  -0.0769   0.7429   0.1728
  -4.500  -0.1121   0.02719   0.01580  -0.0764   0.7311   0.1887
  -4.250  -0.0871   0.02655   0.01532  -0.0760   0.7222   0.2156
  -4.000  -0.0642   0.02619   0.01526  -0.0754   0.7120   0.2630
  -3.750  -0.0385   0.02603   0.01507  -0.0748   0.7047   0.3225
  -3.500  -0.0156   0.02610   0.01514  -0.0741   0.6954   0.3639
  -3.250   0.0098   0.02609   0.01505  -0.0735   0.6885   0.3973
  -3.000   0.0348   0.02613   0.01502  -0.0730   0.6812   0.4250
  -2.750   0.0594   0.02615   0.01505  -0.0723   0.6739   0.4506
  -2.500   0.0850   0.02613   0.01499  -0.0716   0.6683   0.4839
  -2.250   0.1073   0.02623   0.01525  -0.0705   0.6618   0.5177
  -2.000   0.1308   0.02630   0.01540  -0.0695   0.6555   0.5494
  -1.750   0.1570   0.02626   0.01537  -0.0689   0.6505   0.5747
  -1.500   0.1834   0.02626   0.01535  -0.0685   0.6453   0.5949
  -1.250   0.2078   0.02638   0.01551  -0.0682   0.6390   0.6137
  -1.000   0.2341   0.02640   0.01555  -0.0678   0.6339   0.6356
  -0.750   0.2614   0.02635   0.01552  -0.0673   0.6299   0.6628
  -0.500   0.2849   0.02653   0.01584  -0.0665   0.6248   0.6960
  -0.250   0.3081   0.02675   0.01622  -0.0655   0.6191   0.7387
   0.000   0.3372   0.02686   0.01645  -0.0651   0.6144   0.7968
   0.250   0.3799   0.02696   0.01653  -0.0671   0.6105   0.8673
   0.500   0.4262   0.02745   0.01699  -0.0709   0.6052   0.9351
   0.750   0.4785   0.02795   0.01740  -0.0765   0.5992   0.9901
   1.000   0.5066   0.02830   0.01757  -0.0773   0.5946   1.0000
   1.250   0.5293   0.02859   0.01766  -0.0766   0.5910   1.0000
   1.500   0.5442   0.02936   0.01837  -0.0753   0.5859   1.0000
   1.750   0.5591   0.03017   0.01913  -0.0739   0.5802   1.0000
   2.000   0.5807   0.03066   0.01950  -0.0731   0.5754   1.0000
   2.250   0.6080   0.03085   0.01953  -0.0728   0.5713   1.0000
   2.500   0.6193   0.03189   0.02058  -0.0710   0.5638   1.0000
   2.750   0.6405   0.03229   0.02090  -0.0700   0.5564   1.0000
   3.000   0.6737   0.03202   0.02043  -0.0701   0.5509   1.0000
   3.250   0.6811   0.03315   0.02161  -0.0678   0.5407   1.0000
   3.500   0.7093   0.03312   0.02146  -0.0673   0.5340   1.0000
   3.750   0.7303   0.03358   0.02186  -0.0663   0.5271   1.0000
   4.000   0.7429   0.03456   0.02287  -0.0647   0.5190   1.0000
   4.250   0.7706   0.03472   0.02296  -0.0644   0.5139   1.0000
   4.500   0.7909   0.03535   0.02357  -0.0635   0.5081   1.0000
   4.750   0.7971   0.03674   0.02505  -0.0613   0.4996   1.0000
   5.000   0.8249   0.03690   0.02516  -0.0610   0.4944   1.0000
   5.250   0.8434   0.03764   0.02590  -0.0599   0.4884   1.0000
   5.500   0.8441   0.03937   0.02774  -0.0574   0.4793   1.0000
   5.750   0.8740   0.03939   0.02772  -0.0572   0.4746   1.0000
   6.000   0.8695   0.04145   0.02989  -0.0543   0.4652   1.0000
   6.250   0.8847   0.04227   0.03074  -0.0530   0.4581   1.0000
   6.500   0.9218   0.04178   0.03019  -0.0533   0.4542   1.0000
   6.750   0.8870   0.04556   0.03412  -0.0482   0.4410   1.0000
   7.000   0.9229   0.04505   0.03359  -0.0483   0.4369   1.0000
   7.500   0.9174   0.04913   0.03777  -0.0438   0.4193   1.0000
   8.000   0.8605   0.05994   0.04874  -0.0415   0.3916   1.0000
   8.250   0.8790   0.06075   0.04957  -0.0408   0.3871   1.0000
   8.500   0.9071   0.06046   0.04929  -0.0400   0.3847   1.0000
   9.000   0.8505   0.07426   0.06319  -0.0412   0.3599   1.0000
   9.250   0.8629   0.07601   0.06498  -0.0408   0.3555   1.0000
   9.500   0.8847   0.07651   0.06550  -0.0402   0.3531   1.0000
  10.000   0.8572   0.08758   0.07668  -0.0417   0.3395   1.0000
  10.250   0.8749   0.08888   0.07802  -0.0413   0.3375   1.0000
  10.500   0.8375   0.09791   0.08711  -0.0434   0.3296   1.0000
  10.750   0.8439   0.10069   0.08994  -0.0436   0.3256   1.0000
  11.000   0.8624   0.10176   0.09108  -0.0432   0.3228   1.0000
  11.250   0.8526   0.10694   0.09632  -0.0442   0.3181   1.0000
  11.500   0.8434   0.11189   0.10134  -0.0453   0.3126   1.0000
  11.750   0.8611   0.11292   0.10242  -0.0449   0.3086   1.0000
  12.000   0.8853   0.11291   0.10247  -0.0441   0.3053   1.0000
  12.250   0.8644   0.11906   0.10869  -0.0458   0.2959   1.0000
  12.500   0.8879   0.11903   0.10872  -0.0449   0.2920   1.0000
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