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GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il)
Reynolds number: 200,000
Max Cl/Cd: 68.97 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe290-il-200000.txt
Download as CSV file: xf-goe290-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3310   0.10770   0.10396  -0.0408   1.0000   0.0979
 -10.750  -0.7104   0.05413   0.04952  -0.0669   1.0000   0.0680
 -10.500  -0.7131   0.05238   0.04780  -0.0640   1.0000   0.0684
 -10.250  -0.7061   0.05100   0.04647  -0.0624   0.9990   0.0690
  -9.750  -0.6852   0.03912   0.03310  -0.0694   0.9821   0.0679
  -9.500  -0.6526   0.03647   0.03036  -0.0720   0.9750   0.0687
  -9.250  -0.6128   0.03467   0.02853  -0.0754   0.9699   0.0700
  -9.000  -0.5793   0.03276   0.02644  -0.0777   0.9611   0.0714
  -8.750  -0.5450   0.03066   0.02404  -0.0800   0.9533   0.0728
  -8.500  -0.5176   0.02886   0.02194  -0.0805   0.9392   0.0739
  -8.250  -0.4918   0.02744   0.02019  -0.0803   0.9222   0.0750
  -8.000  -0.4681   0.02582   0.01837  -0.0797   0.9002   0.0762
  -7.750  -0.4417   0.02452   0.01706  -0.0794   0.8773   0.0779
  -7.500  -0.4157   0.02362   0.01603  -0.0787   0.8527   0.0799
  -7.250  -0.3916   0.02282   0.01501  -0.0777   0.8248   0.0819
  -7.000  -0.3676   0.02217   0.01404  -0.0766   0.7982   0.0837
  -6.750  -0.3434   0.02124   0.01290  -0.0758   0.7730   0.0856
  -6.500  -0.3187   0.02049   0.01211  -0.0752   0.7499   0.0881
  -6.250  -0.2933   0.02000   0.01149  -0.0747   0.7297   0.0912
  -6.000  -0.2674   0.01959   0.01087  -0.0741   0.7123   0.0942
  -5.750  -0.2423   0.01878   0.01001  -0.0737   0.6979   0.0974
  -5.500  -0.2164   0.01830   0.00950  -0.0733   0.6842   0.1011
  -5.250  -0.1897   0.01797   0.00904  -0.0730   0.6727   0.1054
  -5.000  -0.1643   0.01740   0.00845  -0.0726   0.6634   0.1101
  -4.750  -0.1375   0.01707   0.00810  -0.0724   0.6544   0.1156
  -4.500  -0.1113   0.01666   0.00766  -0.0722   0.6467   0.1218
  -4.250  -0.0843   0.01640   0.00736  -0.0720   0.6397   0.1295
  -4.000  -0.0578   0.01600   0.00701  -0.0718   0.6324   0.1392
  -3.750  -0.0312   0.01565   0.00665  -0.0716   0.6264   0.1536
  -3.500  -0.0055   0.01506   0.00628  -0.0715   0.6209   0.1906
  -3.250   0.0197   0.01459   0.00637  -0.0713   0.6154   0.3231
  -3.000   0.0478   0.01468   0.00645  -0.0713   0.6104   0.3616
  -2.750   0.0761   0.01481   0.00650  -0.0712   0.6059   0.3850
  -2.500   0.1044   0.01486   0.00655  -0.0713   0.6011   0.4030
  -2.250   0.1327   0.01489   0.00657  -0.0713   0.5961   0.4187
  -2.000   0.1614   0.01494   0.00657  -0.0714   0.5917   0.4336
  -1.750   0.1897   0.01498   0.00659  -0.0714   0.5878   0.4486
  -1.500   0.2179   0.01502   0.00666  -0.0714   0.5837   0.4641
  -1.250   0.2460   0.01499   0.00669  -0.0715   0.5790   0.4796
  -1.000   0.2741   0.01498   0.00670  -0.0715   0.5741   0.4963
  -0.750   0.3024   0.01497   0.00669  -0.0714   0.5695   0.5149
  -0.500   0.3303   0.01501   0.00677  -0.0714   0.5652   0.5355
  -0.250   0.3574   0.01491   0.00685  -0.0713   0.5605   0.5610
   0.000   0.3846   0.01482   0.00691  -0.0711   0.5561   0.5955
   0.250   0.4108   0.01467   0.00699  -0.0706   0.5524   0.6462
   0.500   0.4348   0.01450   0.00714  -0.0694   0.5491   0.7354
   0.750   0.4571   0.01440   0.00742  -0.0673   0.5452   0.8532
   1.000   0.4951   0.01448   0.00761  -0.0686   0.5404   0.9346
   1.250   0.5446   0.01465   0.00772  -0.0728   0.5359   0.9723
   1.500   0.5984   0.01483   0.00776  -0.0780   0.5312   0.9926
   1.750   0.6405   0.01503   0.00787  -0.0811   0.5265   1.0000
   2.000   0.6624   0.01513   0.00798  -0.0802   0.5217   1.0000
   2.250   0.6856   0.01525   0.00804  -0.0794   0.5172   1.0000
   2.500   0.7100   0.01540   0.00811  -0.0789   0.5134   1.0000
   2.750   0.7354   0.01565   0.00822  -0.0784   0.5099   1.0000
   3.000   0.7584   0.01583   0.00845  -0.0776   0.5057   1.0000
   3.250   0.7821   0.01599   0.00863  -0.0769   0.5011   1.0000
   3.500   0.8071   0.01613   0.00873  -0.0764   0.4969   1.0000
   3.750   0.8334   0.01630   0.00881  -0.0761   0.4931   1.0000
   4.000   0.8592   0.01655   0.00902  -0.0758   0.4892   1.0000
   4.250   0.8828   0.01669   0.00924  -0.0751   0.4838   1.0000
   4.500   0.9084   0.01678   0.00932  -0.0747   0.4786   1.0000
   4.750   0.9357   0.01688   0.00933  -0.0745   0.4740   1.0000
   5.000   0.9606   0.01706   0.00953  -0.0740   0.4689   1.0000
   5.250   0.9850   0.01717   0.00970  -0.0734   0.4629   1.0000
   5.500   1.0115   0.01723   0.00973  -0.0732   0.4577   1.0000
   5.750   1.0379   0.01735   0.00979  -0.0729   0.4524   1.0000
   6.000   1.0609   0.01739   0.00994  -0.0721   0.4446   1.0000
   6.250   1.0870   0.01733   0.00979  -0.0717   0.4378   1.0000
   6.500   1.1096   0.01738   0.00993  -0.0708   0.4290   1.0000
   6.750   1.1341   0.01734   0.00985  -0.0701   0.4209   1.0000
   7.000   1.1564   0.01744   0.01001  -0.0692   0.4113   1.0000
   7.250   1.1798   0.01747   0.00997  -0.0684   0.4024   1.0000
   7.500   1.2008   0.01761   0.01020  -0.0673   0.3907   1.0000
   7.750   1.2222   0.01779   0.01039  -0.0663   0.3799   1.0000
   8.000   1.2428   0.01802   0.01055  -0.0651   0.3694   1.0000
   8.250   1.2624   0.01832   0.01088  -0.0639   0.3571   1.0000
   8.500   1.2810   0.01869   0.01125  -0.0626   0.3455   1.0000
   8.750   1.2981   0.01911   0.01162  -0.0610   0.3343   1.0000
   9.000   1.3137   0.01960   0.01206  -0.0592   0.3231   1.0000
   9.250   1.3291   0.02012   0.01259  -0.0575   0.3130   1.0000
   9.500   1.3408   0.02070   0.01311  -0.0551   0.3050   1.0000
   9.750   1.3540   0.02129   0.01374  -0.0531   0.2973   1.0000
  10.000   1.3652   0.02200   0.01440  -0.0509   0.2910   1.0000
  10.250   1.3785   0.02268   0.01515  -0.0491   0.2844   1.0000
  10.500   1.3888   0.02351   0.01597  -0.0471   0.2776   1.0000
  10.750   1.4000   0.02438   0.01685  -0.0454   0.2717   1.0000
  11.000   1.4108   0.02529   0.01782  -0.0437   0.2655   1.0000
  11.250   1.4190   0.02639   0.01890  -0.0419   0.2599   1.0000
  11.500   1.4297   0.02743   0.02003  -0.0405   0.2543   1.0000
  11.750   1.4377   0.02867   0.02132  -0.0391   0.2483   1.0000
  12.000   1.4437   0.03013   0.02276  -0.0376   0.2427   1.0000
  12.250   1.4523   0.03150   0.02427  -0.0367   0.2370   1.0000
  12.500   1.4574   0.03318   0.02598  -0.0355   0.2313   1.0000
  12.750   1.4622   0.03495   0.02780  -0.0346   0.2259   1.0000
  13.000   1.4660   0.03693   0.02989  -0.0338   0.2190   1.0000
  13.250   1.4662   0.03923   0.03218  -0.0330   0.2131   1.0000
  13.500   1.4704   0.04138   0.03449  -0.0326   0.2066   1.0000
  13.750   1.4691   0.04404   0.03720  -0.0322   0.1999   1.0000
  14.000   1.4690   0.04677   0.04004  -0.0320   0.1916   1.0000
  14.250   1.4648   0.04998   0.04331  -0.0320   0.1828   1.0000
  14.500   1.4621   0.05319   0.04661  -0.0321   0.1690   1.0000
  14.750   1.4448   0.05810   0.05145  -0.0325   0.1384   1.0000
  15.000   1.4179   0.06426   0.05746  -0.0330   0.1216   1.0000
  15.250   1.3976   0.06970   0.06287  -0.0335   0.1122   1.0000
  15.500   1.3816   0.07478   0.06797  -0.0341   0.1042   1.0000
  15.750   1.3678   0.07969   0.07294  -0.0347   0.0969   1.0000
  16.000   1.3542   0.08469   0.07798  -0.0355   0.0898   1.0000
  16.250   1.3443   0.08931   0.08268  -0.0363   0.0799   1.0000
  16.500   1.3308   0.09452   0.08792  -0.0374   0.0696   1.0000
  16.750   1.3156   0.10007   0.09348  -0.0387   0.0639   1.0000
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