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GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 389 AIRFOIL (goe389-il)
Reynolds number: 500,000
Max Cl/Cd: 101.37 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe389-il-500000.txt
Download as CSV file: xf-goe389-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 389 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3526   0.09310   0.09086  -0.0332   1.0000   0.0264
  -8.750  -0.3526   0.08956   0.08735  -0.0349   1.0000   0.0278
  -8.500  -0.3638   0.08501   0.08287  -0.0385   1.0000   0.0292
  -8.250  -0.3051   0.06502   0.06309  -0.0456   0.9958   0.0300
  -8.000  -0.2917   0.06136   0.05942  -0.0480   0.9924   0.0305
  -7.750  -0.3633   0.07054   0.06848  -0.0520   0.9941   0.0295
  -7.500  -0.3523   0.06118   0.05908  -0.0623   0.9874   0.0304
  -7.250  -0.3252   0.05847   0.05633  -0.0665   0.9841   0.0312
  -7.000  -0.2990   0.05515   0.05296  -0.0714   0.9777   0.0326
  -6.750  -0.2600   0.04342   0.04060  -0.0868   0.9696   0.0374
  -6.500  -0.2467   0.03511   0.03206  -0.0914   0.9599   0.0391
  -6.250  -0.2195   0.03360   0.03051  -0.0928   0.9511   0.0403
  -6.000  -0.1908   0.03146   0.02821  -0.0947   0.9427   0.0426
  -5.750  -0.1681   0.02340   0.01903  -0.0956   0.9305   0.0371
  -5.500  -0.1419   0.02190   0.01719  -0.0955   0.9184   0.0374
  -5.250  -0.1182   0.01926   0.01415  -0.0953   0.9060   0.0376
  -5.000  -0.0935   0.01722   0.01178  -0.0949   0.8941   0.0377
  -4.750  -0.0679   0.01567   0.00997  -0.0945   0.8830   0.0378
  -4.500  -0.0424   0.01416   0.00823  -0.0941   0.8713   0.0382
  -4.250  -0.0166   0.01300   0.00694  -0.0937   0.8593   0.0393
  -4.000   0.0099   0.01236   0.00621  -0.0933   0.8477   0.0402
  -3.750   0.0367   0.01179   0.00555  -0.0930   0.8364   0.0408
  -3.250   0.0905   0.01088   0.00447  -0.0923   0.8124   0.0423
  -3.000   0.1175   0.01050   0.00402  -0.0920   0.8006   0.0431
  -2.750   0.1447   0.01020   0.00364  -0.0917   0.7897   0.0443
  -2.500   0.1720   0.00997   0.00332  -0.0915   0.7790   0.0458
  -2.250   0.1993   0.00976   0.00302  -0.0912   0.7680   0.0468
  -2.000   0.2265   0.00943   0.00263  -0.0910   0.7576   0.0489
  -1.750   0.2540   0.00925   0.00240  -0.0908   0.7478   0.0523
  -1.500   0.2816   0.00915   0.00225  -0.0906   0.7375   0.0566
  -1.250   0.3092   0.00898   0.00208  -0.0904   0.7270   0.0702
  -1.000   0.3359   0.00853   0.00193  -0.0903   0.7168   0.1685
  -0.750   0.3626   0.00824   0.00192  -0.0902   0.7059   0.2795
  -0.500   0.3896   0.00802   0.00190  -0.0901   0.6937   0.3535
  -0.250   0.4151   0.00755   0.00192  -0.0898   0.6796   0.5265
   0.000   0.4385   0.00703   0.00193  -0.0889   0.6632   0.7071
   0.250   0.4750   0.00651   0.00194  -0.0900   0.6401   0.9954
   0.500   0.5027   0.00662   0.00189  -0.0899   0.6097   1.0000
   0.750   0.5275   0.00682   0.00187  -0.0892   0.5732   1.0000
   1.000   0.5521   0.00708   0.00190  -0.0885   0.5411   1.0000
   1.250   0.5774   0.00732   0.00198  -0.0880   0.5168   1.0000
   1.500   0.6031   0.00755   0.00206  -0.0876   0.4985   1.0000
   1.750   0.6292   0.00775   0.00215  -0.0872   0.4839   1.0000
   2.000   0.6558   0.00792   0.00224  -0.0870   0.4724   1.0000
   2.250   0.6824   0.00810   0.00235  -0.0867   0.4628   1.0000
   2.500   0.7089   0.00828   0.00245  -0.0865   0.4537   1.0000
   2.750   0.7359   0.00843   0.00256  -0.0863   0.4457   1.0000
   3.000   0.7624   0.00862   0.00269  -0.0860   0.4379   1.0000
   3.250   0.7894   0.00876   0.00282  -0.0859   0.4312   1.0000
   3.500   0.8161   0.00893   0.00295  -0.0857   0.4246   1.0000
   3.750   0.8429   0.00910   0.00311  -0.0855   0.4182   1.0000
   4.000   0.8695   0.00926   0.00324  -0.0853   0.4097   1.0000
   4.250   0.8962   0.00941   0.00338  -0.0851   0.4008   1.0000
   4.500   0.9223   0.00961   0.00353  -0.0848   0.3922   1.0000
   4.750   0.9492   0.00974   0.00368  -0.0846   0.3832   1.0000
   5.000   0.9754   0.00991   0.00383  -0.0844   0.3724   1.0000
   5.250   1.0013   0.01011   0.00398  -0.0841   0.3617   1.0000
   5.500   1.0278   0.01026   0.00415  -0.0839   0.3503   1.0000
   5.750   1.0538   0.01045   0.00432  -0.0836   0.3373   1.0000
   6.000   1.0796   0.01065   0.00451  -0.0833   0.3250   1.0000
   6.250   1.1048   0.01091   0.00472  -0.0830   0.3079   1.0000
   6.500   1.1287   0.01127   0.00498  -0.0824   0.2804   1.0000
   6.750   1.1503   0.01185   0.00534  -0.0816   0.2397   1.0000
   7.000   1.1676   0.01286   0.00596  -0.0801   0.1727   1.0000
   7.250   1.1835   0.01403   0.00677  -0.0785   0.1190   1.0000
   7.500   1.2039   0.01472   0.00736  -0.0775   0.0978   1.0000
   7.750   1.2194   0.01585   0.00817  -0.0758   0.0503   1.0000
   8.000   1.2351   0.01691   0.00905  -0.0741   0.0219   1.0000
   8.250   1.2555   0.01750   0.00969  -0.0730   0.0189   1.0000
   8.500   1.2749   0.01815   0.01041  -0.0717   0.0176   1.0000
   8.750   1.2929   0.01888   0.01123  -0.0703   0.0166   1.0000
   9.000   1.3084   0.01976   0.01221  -0.0685   0.0157   1.0000
   9.250   1.3227   0.02066   0.01321  -0.0665   0.0151   1.0000
   9.500   1.3356   0.02146   0.01409  -0.0643   0.0146   1.0000
   9.750   1.3458   0.02240   0.01511  -0.0618   0.0141   1.0000
  10.000   1.3541   0.02347   0.01628  -0.0592   0.0137   1.0000
  10.250   1.3609   0.02468   0.01758  -0.0566   0.0134   1.0000
  10.500   1.3660   0.02606   0.01906  -0.0541   0.0131   1.0000
  10.750   1.3693   0.02766   0.02074  -0.0517   0.0128   1.0000
  11.000   1.3710   0.02951   0.02267  -0.0494   0.0126   1.0000
  11.250   1.3712   0.03159   0.02485  -0.0474   0.0124   1.0000
  11.500   1.3698   0.03397   0.02731  -0.0456   0.0122   1.0000
  11.750   1.3671   0.03661   0.03004  -0.0440   0.0120   1.0000
  12.000   1.3643   0.03938   0.03289  -0.0426   0.0119   1.0000
  12.250   1.3621   0.04216   0.03575  -0.0411   0.0117   1.0000
  12.500   1.3612   0.04484   0.03848  -0.0392   0.0116   1.0000
  12.750   1.3662   0.04703   0.04078  -0.0386   0.0115   1.0000
  13.000   1.3705   0.04933   0.04320  -0.0382   0.0113   1.0000
  13.250   1.3740   0.05176   0.04575  -0.0378   0.0111   1.0000
  13.500   1.3767   0.05430   0.04840  -0.0374   0.0109   1.0000
  13.750   1.3786   0.05693   0.05114  -0.0369   0.0107   1.0000
  14.000   1.3803   0.05963   0.05394  -0.0363   0.0106   1.0000
  14.250   1.3818   0.06241   0.05684  -0.0358   0.0106   1.0000
  14.500   1.3826   0.06533   0.05988  -0.0354   0.0105   1.0000
  14.750   1.3827   0.06840   0.06309  -0.0352   0.0104   1.0000
  15.000   1.3818   0.07169   0.06651  -0.0352   0.0104   1.0000
  15.250   1.3799   0.07520   0.07015  -0.0353   0.0104   1.0000
  15.500   1.3766   0.07897   0.07407  -0.0356   0.0104   1.0000
  15.750   1.3719   0.08304   0.07830  -0.0362   0.0104   1.0000
  16.000   1.3657   0.08745   0.08287  -0.0371   0.0104   1.0000
  16.250   1.3582   0.09219   0.08777  -0.0384   0.0104   1.0000
  16.500   1.3490   0.09728   0.09303  -0.0400   0.0105   1.0000
  16.750   1.3386   0.10271   0.09863  -0.0418   0.0106   1.0000
  17.000   1.3271   0.10849   0.10458  -0.0441   0.0107   1.0000
  17.250   1.3146   0.11459   0.11084  -0.0468   0.0108   1.0000
  17.500   1.3012   0.12096   0.11738  -0.0497   0.0109   1.0000
  17.750   1.2867   0.12766   0.12423  -0.0528   0.0111   1.0000
  18.500   1.0181   0.12804   0.12506  -0.0351   0.0117   1.0000
  18.750   1.0030   0.13316   0.13030  -0.0385   0.0118   1.0000
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