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GOE 571 AIRFOIL (goe571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 571 AIRFOIL (goe571-il)
Reynolds number: 1,000,000
Max Cl/Cd: 62.85 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe571-il-1000000.txt
Download as CSV file: xf-goe571-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 571 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.5147   0.09527   0.09094  -0.1702   0.5414   0.0230
 -11.750   0.5228   0.09322   0.08889  -0.1708   0.5380   0.0231
 -11.500   0.5313   0.09133   0.08698  -0.1715   0.5341   0.0233
 -11.250   0.5393   0.08944   0.08507  -0.1720   0.5297   0.0236
 -11.000   0.5465   0.08741   0.08303  -0.1727   0.5261   0.0238
 -10.750   0.5527   0.08523   0.08087  -0.1733   0.5230   0.0240
 -10.500   0.5589   0.08314   0.07877  -0.1739   0.5191   0.0246
 -10.250   0.5639   0.08093   0.07656  -0.1745   0.5152   0.0248
 -10.000   0.5414   0.07487   0.07052  -0.1777   0.5135   0.0261
  -9.750   0.5435   0.07237   0.06799  -0.1783   0.5085   0.0261
  -9.500   0.5432   0.06960   0.06526  -0.1783   0.5061   0.0263
  -9.250   0.5474   0.06765   0.06331  -0.1783   0.5013   0.0264
  -9.000   0.5529   0.06604   0.06170  -0.1782   0.4975   0.0265
  -8.750   0.5547   0.06410   0.05974  -0.1781   0.4920   0.0266
  -8.500   0.5546   0.06196   0.05761  -0.1781   0.4883   0.0266
  -8.250   0.5557   0.06010   0.05577  -0.1780   0.4849   0.0267
  -8.000   0.5495   0.05758   0.05328  -0.1779   0.4814   0.0268
  -7.750   0.5438   0.05551   0.05121  -0.1775   0.4772   0.0270
  -7.500   0.5205   0.05211   0.04784  -0.1783   0.4741   0.0271
  -7.250   0.4879   0.04929   0.04503  -0.1751   0.4715   0.0271
  -7.000   0.4497   0.04746   0.04322  -0.1678   0.4700   0.0271
  -6.750   0.4253   0.04571   0.04147  -0.1618   0.4676   0.0272
  -6.500   0.4039   0.04371   0.03944  -0.1562   0.4648   0.0273
  -6.250   0.3861   0.04197   0.03765  -0.1504   0.4620   0.0274
  -6.000   0.3702   0.04032   0.03593  -0.1445   0.4588   0.0276
  -5.750   0.3580   0.03875   0.03428  -0.1390   0.4549   0.0278
  -5.500   0.2926   0.03238   0.02730  -0.1240   0.4547   0.0299
  -5.250   0.2628   0.02876   0.02342  -0.1151   0.4534   0.0302
  -5.000   0.2719   0.02772   0.02240  -0.1122   0.4508   0.0303
  -4.750   0.2766   0.02681   0.02143  -0.1084   0.4480   0.0304
  -4.500   0.2866   0.02637   0.02099  -0.1055   0.4448   0.0306
  -4.250   0.2905   0.02556   0.02008  -0.1014   0.4415   0.0307
  -4.000   0.2987   0.02529   0.01977  -0.0980   0.4378   0.0309
  -3.750   0.3056   0.02456   0.01897  -0.0944   0.4358   0.0311
  -3.500   0.3161   0.02406   0.01842  -0.0914   0.4338   0.0316
  -3.250   0.3236   0.02327   0.01751  -0.0876   0.4312   0.0318
  -3.000   0.3138   0.02159   0.01531  -0.0799   0.4296   0.0345
  -2.750   0.3254   0.02112   0.01481  -0.0771   0.4270   0.0347
  -2.500   0.3378   0.02083   0.01452  -0.0745   0.4246   0.0351
  -2.250   0.3470   0.02050   0.01411  -0.0711   0.4217   0.0353
  -2.000   0.3585   0.02036   0.01393  -0.0682   0.4192   0.0359
  -1.750   0.3720   0.01994   0.01342  -0.0655   0.4181   0.0367
  -1.500   0.3812   0.01942   0.01268  -0.0618   0.4166   0.0391
  -1.250   0.3964   0.01907   0.01233  -0.0596   0.4150   0.0395
  -1.000   0.4111   0.01885   0.01208  -0.0573   0.4132   0.0399
  -0.750   0.4253   0.01869   0.01188  -0.0549   0.4112   0.0410
  -0.500   0.4357   0.01857   0.01159  -0.0517   0.4093   0.0438
  -0.250   0.4486   0.01842   0.01142  -0.0492   0.4067   0.0442
   0.000   0.4620   0.01837   0.01134  -0.0469   0.4044   0.0453
   0.250   0.4905   0.01716   0.00967  -0.0456   0.4022   0.0299
   0.500   0.5112   0.01689   0.00938  -0.0446   0.4013   0.0301
   0.750   0.5310   0.01683   0.00932  -0.0434   0.4002   0.0300
   1.000   0.5516   0.01671   0.00921  -0.0424   0.3987   0.0301
   1.250   0.5735   0.01646   0.00900  -0.0418   0.3974   0.0308
   1.500   0.5925   0.01651   0.00906  -0.0406   0.3958   0.0311
   1.750   0.6112   0.01663   0.00918  -0.0395   0.3941   0.0316
   2.000   0.6304   0.01678   0.00932  -0.0384   0.3925   0.0319
   2.250   0.6485   0.01699   0.00952  -0.0373   0.3903   0.0323
   2.500   0.6666   0.01727   0.00978  -0.0363   0.3880   0.0325
   2.750   0.6878   0.01749   0.00998  -0.0359   0.3858   0.0328
   3.000   0.7118   0.01764   0.01015  -0.0359   0.3851   0.0332
   3.250   0.7347   0.01786   0.01039  -0.0358   0.3841   0.0334
   3.500   0.7585   0.01810   0.01064  -0.0359   0.3830   0.0337
   3.750   0.7829   0.01834   0.01090  -0.0362   0.3818   0.0341
   4.000   0.8121   0.01854   0.01112  -0.0376   0.3802   0.0358
   4.250   0.8361   0.01887   0.01146  -0.0379   0.3787   0.0360
   4.500   0.8606   0.01923   0.01183  -0.0385   0.3773   0.0372
   4.750   0.8859   0.01961   0.01221  -0.0393   0.3758   0.0394
   5.000   0.9116   0.02006   0.01266  -0.0403   0.3739   0.0418
   5.250   0.9441   0.02048   0.01318  -0.0428   0.3717   0.0813
   5.500   1.2532   0.01994   0.01480  -0.1015   0.3686   1.0000
   5.750   1.2688   0.02047   0.01533  -0.1004   0.3676   1.0000
   6.000   1.2851   0.02097   0.01584  -0.0995   0.3665   1.0000
   6.250   1.3004   0.02155   0.01643  -0.0985   0.3653   1.0000
   6.500   1.3153   0.02216   0.01704  -0.0975   0.3638   1.0000
   6.750   1.3306   0.02277   0.01764  -0.0966   0.3625   1.0000
   7.000   1.3443   0.02348   0.01836  -0.0955   0.3613   1.0000
   7.250   1.3572   0.02426   0.01912  -0.0944   0.3594   1.0000
   7.500   1.3685   0.02515   0.02000  -0.0932   0.3577   1.0000
   7.750   1.3800   0.02602   0.02085  -0.0921   0.3554   1.0000
   8.000   1.3953   0.02667   0.02148  -0.0913   0.3537   1.0000
   8.250   1.4083   0.02755   0.02240  -0.0905   0.3529   1.0000
   8.500   1.4224   0.02837   0.02324  -0.0899   0.3519   1.0000
   8.750   1.4357   0.02925   0.02415  -0.0892   0.3507   1.0000
   9.000   1.4487   0.03017   0.02509  -0.0885   0.3494   1.0000
   9.250   1.4619   0.03109   0.02603  -0.0879   0.3478   1.0000
   9.500   1.4729   0.03217   0.02713  -0.0871   0.3463   1.0000
   9.750   1.4840   0.03325   0.02821  -0.0864   0.3447   1.0000
  10.000   1.4934   0.03446   0.02943  -0.0856   0.3429   1.0000
  10.250   1.5020   0.03570   0.03065  -0.0847   0.3407   1.0000
  10.500   1.5151   0.03653   0.03147  -0.0841   0.3384   1.0000
  10.750   1.5253   0.03779   0.03277  -0.0835   0.3375   1.0000
  11.000   1.5351   0.03906   0.03409  -0.0830   0.3363   1.0000
  11.250   1.5461   0.04024   0.03531  -0.0825   0.3348   1.0000
  11.500   1.5541   0.04168   0.03679  -0.0819   0.3331   1.0000
  11.750   1.5635   0.04301   0.03814  -0.0814   0.3314   1.0000
  12.000   1.5705   0.04452   0.03966  -0.0807   0.3293   1.0000
  12.250   1.5748   0.04623   0.04138  -0.0799   0.3271   1.0000
  12.500   1.5838   0.04750   0.04263  -0.0793   0.3247   1.0000
  12.750   1.5866   0.04947   0.04465  -0.0786   0.3220   1.0000
  13.000   1.5968   0.05074   0.04596  -0.0783   0.3213   1.0000
  13.250   1.6029   0.05243   0.04770  -0.0778   0.3190   1.0000
  13.500   1.6042   0.05456   0.04987  -0.0771   0.3161   1.0000
  13.750   1.6106   0.05617   0.05150  -0.0766   0.3144   1.0000
  14.000   1.6138   0.05806   0.05338  -0.0760   0.3118   1.0000
  14.250   1.6110   0.06054   0.05589  -0.0752   0.3079   1.0000
  14.500   1.6167   0.06232   0.05772  -0.0748   0.3062   1.0000
  14.750   1.6195   0.06436   0.05981  -0.0744   0.3037   1.0000
  15.000   1.6178   0.06683   0.06231  -0.0737   0.3006   1.0000
  15.250   1.6156   0.06930   0.06477  -0.0731   0.2972   1.0000
  15.500   1.6150   0.07163   0.06712  -0.0725   0.2944   1.0000
  15.750   1.6154   0.07398   0.06955  -0.0721   0.2920   1.0000
  16.000   1.6113   0.07679   0.07240  -0.0716   0.2883   1.0000
  16.250   1.6039   0.07991   0.07552  -0.0709   0.2844   1.0000
  16.500   1.6003   0.08259   0.07820  -0.0704   0.2807   1.0000
  16.750   1.5971   0.08536   0.08105  -0.0700   0.2786   1.0000
  17.000   1.5950   0.08801   0.08374  -0.0697   0.2751   1.0000
  17.250   1.5827   0.09173   0.08748  -0.0691   0.2711   1.0000
  17.500   1.5758   0.09489   0.09064  -0.0687   0.2667   1.0000
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