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GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 14 AIRFOIL (goe14-il)
Reynolds number: 500,000
Max Cl/Cd: 98.6 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe14-il-500000.txt
Download as CSV file: xf-goe14-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14 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  -0.0725   0.09294   0.09051  -0.0400   0.8620   0.0247
  -8.750  -0.0674   0.09016   0.08771  -0.0413   0.8519   0.0250
  -8.500  -0.0641   0.08763   0.08512  -0.0429   0.8429   0.0251
  -7.500  -0.1112   0.08831   0.08570  -0.0435   0.8354   0.0252
  -7.250  -0.1007   0.08536   0.08269  -0.0433   0.8263   0.0253
  -7.000  -0.0891   0.08271   0.08004  -0.0444   0.8168   0.0255
  -6.750  -0.0758   0.08015   0.07742  -0.0463   0.8077   0.0257
  -6.500  -0.0606   0.07754   0.07479  -0.0489   0.7983   0.0259
  -6.250  -0.0444   0.07492   0.07212  -0.0517   0.7891   0.0263
  -6.000  -0.0262   0.07219   0.06936  -0.0550   0.7799   0.0267
  -5.750  -0.0067   0.06942   0.06652  -0.0584   0.7708   0.0273
  -5.500   0.0163   0.06647   0.06352  -0.0628   0.7613   0.0281
  -5.000   0.0735   0.05992   0.05679  -0.0748   0.7417   0.0287
  -4.500   0.1127   0.05497   0.05174  -0.0774   0.7205   0.0292
  -4.250   0.1369   0.05263   0.04932  -0.0798   0.7089   0.0295
  -4.000   0.1628   0.05029   0.04689  -0.0824   0.6961   0.0301
  -3.750   0.1905   0.04789   0.04439  -0.0852   0.6821   0.0310
  -3.500   0.2393   0.04504   0.04124  -0.0922   0.6675   0.0323
  -3.250   0.2576   0.04255   0.03871  -0.0924   0.6506   0.0325
  -3.000   0.2800   0.04057   0.03663  -0.0932   0.6316   0.0328
  -2.750   0.3052   0.03882   0.03474  -0.0943   0.6108   0.0332
  -2.500   0.3323   0.03716   0.03291  -0.0956   0.5898   0.0340
  -2.250   0.3762   0.03575   0.03111  -0.0984   0.5709   0.0362
  -2.000   0.3987   0.03347   0.02872  -0.0990   0.5538   0.0364
  -1.750   0.4220   0.03182   0.02698  -0.0995   0.5389   0.0368
  -1.500   0.4479   0.03047   0.02552  -0.1001   0.5260   0.0373
  -1.250   0.4754   0.02923   0.02412  -0.1006   0.5142   0.0384
  -1.000   0.5121   0.02773   0.02232  -0.1014   0.5040   0.0407
  -0.750   0.5362   0.02633   0.02085  -0.1018   0.4942   0.0411
  -0.500   0.5628   0.02525   0.01969  -0.1021   0.4849   0.0419
  -0.250   0.5909   0.02430   0.01859  -0.1023   0.4766   0.0436
   0.000   0.6231   0.02311   0.01719  -0.1024   0.4689   0.0456
   0.250   0.6488   0.02219   0.01617  -0.1026   0.4609   0.0464
   0.500   0.6769   0.02135   0.01525  -0.1027   0.4534   0.0478
   0.750   0.7091   0.02063   0.01421  -0.1022   0.4459   0.0504
   1.000   0.7351   0.01962   0.01316  -0.1025   0.4387   0.0510
   1.250   0.7625   0.01892   0.01239  -0.1025   0.4315   0.0523
   1.500   0.7936   0.01904   0.01216  -0.1016   0.4247   0.0555
   1.750   0.8208   0.01768   0.01077  -0.1018   0.4185   0.0560
   2.000   0.8473   0.01706   0.01012  -0.1019   0.4117   0.0573
   2.250   0.8745   0.01669   0.00962  -0.1016   0.4053   0.0594
   2.500   0.9031   0.01606   0.00889  -0.1014   0.3992   0.0593
   2.750   0.9336   0.01354   0.00589  -0.1005   0.3938   0.0504
   3.000   0.9599   0.01394   0.00630  -0.1003   0.3873   0.0520
   3.250   0.9876   0.01347   0.00576  -0.1000   0.3812   0.0563
   3.500   1.0142   0.01361   0.00587  -0.0998   0.3745   0.0596
   3.750   1.0408   0.01368   0.00591  -0.0995   0.3682   0.0648
   4.000   1.0676   0.01369   0.00591  -0.0993   0.3613   0.0715
   4.250   1.0933   0.01377   0.00591  -0.0990   0.3540   0.0784
   4.500   1.1202   0.01374   0.00591  -0.0988   0.3474   0.0860
   4.750   1.1462   0.01386   0.00595  -0.0985   0.3405   0.0931
   5.000   1.1718   0.01385   0.00597  -0.0982   0.3347   0.0982
   5.250   1.1983   0.01390   0.00603  -0.0980   0.3290   0.1003
   5.500   1.2239   0.01404   0.00612  -0.0976   0.3232   0.1013
   5.750   1.2493   0.01411   0.00619  -0.0972   0.3177   0.1021
   6.000   1.2754   0.01413   0.00625  -0.0970   0.3120   0.1026
   6.250   1.3004   0.01427   0.00637  -0.0967   0.3061   0.1041
   6.500   1.3254   0.01445   0.00656  -0.0963   0.3010   0.1058
   6.750   1.3511   0.01458   0.00673  -0.0960   0.2963   0.1068
   7.000   1.3759   0.01478   0.00693  -0.0956   0.2914   0.1080
   7.250   1.3995   0.01509   0.00720  -0.0951   0.2862   0.1096
   7.500   1.4250   0.01524   0.00741  -0.0948   0.2819   0.1117
   7.750   1.4495   0.01544   0.00763  -0.0944   0.2772   0.1143
   8.000   1.4726   0.01575   0.00791  -0.0938   0.2728   0.1171
   8.250   1.4960   0.01605   0.00822  -0.0932   0.2689   0.1206
   8.500   1.5203   0.01626   0.00850  -0.0928   0.2654   0.1264
   8.750   1.5436   0.01653   0.00881  -0.0922   0.2616   0.1464
   9.000   1.5638   0.01586   0.00930  -0.0913   0.2580   1.0000
   9.250   1.5847   0.01632   0.00972  -0.0904   0.2541   1.0000
   9.500   1.6079   0.01658   0.01005  -0.0898   0.2512   1.0000
   9.750   1.6300   0.01690   0.01040  -0.0891   0.2477   1.0000
  10.000   1.6505   0.01730   0.01079  -0.0882   0.2439   1.0000
  10.250   1.6682   0.01783   0.01129  -0.0869   0.2395   1.0000
  10.500   1.6881   0.01814   0.01169  -0.0859   0.2357   1.0000
  10.750   1.7068   0.01852   0.01210  -0.0847   0.2313   1.0000
  11.000   1.7227   0.01905   0.01263  -0.0833   0.2268   1.0000
  11.250   1.7378   0.01965   0.01325  -0.0817   0.2223   1.0000
  11.500   1.7561   0.02007   0.01375  -0.0807   0.2174   1.0000
  11.750   1.7705   0.02073   0.01441  -0.0793   0.2120   1.0000
  12.000   1.7840   0.02148   0.01518  -0.0779   0.2068   1.0000
  12.250   1.8001   0.02209   0.01587  -0.0768   0.2012   1.0000
  12.500   1.8109   0.02307   0.01683  -0.0753   0.1951   1.0000
  12.750   1.8251   0.02387   0.01769  -0.0742   0.1885   1.0000
  13.000   1.8345   0.02503   0.01885  -0.0728   0.1811   1.0000
  13.250   1.8460   0.02610   0.01996  -0.0717   0.1740   1.0000
  13.500   1.8523   0.02759   0.02145  -0.0703   0.1666   1.0000
  13.750   1.8610   0.02896   0.02286  -0.0692   0.1596   1.0000
  14.250   1.8695   0.03258   0.02653  -0.0668   0.1472   1.0000
  14.500   1.8700   0.03482   0.02880  -0.0657   0.1419   1.0000
  14.750   1.8711   0.03706   0.03109  -0.0647   0.1375   1.0000
  15.000   1.8717   0.03942   0.03351  -0.0638   0.1334   1.0000
  15.250   1.8675   0.04233   0.03646  -0.0630   0.1297   1.0000
  15.500   1.8633   0.04533   0.03953  -0.0623   0.1263   1.0000
  15.750   1.8624   0.04808   0.04237  -0.0619   0.1231   1.0000
  16.000   1.8571   0.05143   0.04580  -0.0616   0.1202   1.0000
  16.250   1.8485   0.05527   0.04971  -0.0615   0.1177   1.0000
  16.750   1.8362   0.06270   0.05733  -0.0618   0.1131   1.0000
  17.000   1.8308   0.06641   0.06114  -0.0621   0.1108   1.0000
  17.250   1.8212   0.07071   0.06554  -0.0625   0.1084   1.0000
  17.500   1.8084   0.07553   0.07043  -0.0632   0.1062   1.0000
  17.750   1.7933   0.08068   0.07565  -0.0640   0.1040   1.0000
  18.000   1.7870   0.08468   0.07977  -0.0647   0.1019   1.0000
  18.250   1.7797   0.08887   0.08407  -0.0655   0.0993   1.0000
  18.500   1.7668   0.09391   0.08920  -0.0666   0.0962   1.0000
  18.750   1.7504   0.09946   0.09481  -0.0679   0.0936   1.0000
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