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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 500,000
Max Cl/Cd: 87.92 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe585-il-500000-n5.txt
Download as CSV file: xf-goe585-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7012   0.02632   0.02290  -0.0659   0.9952   0.0135
  -9.250  -0.6799   0.02256   0.01859  -0.0675   0.9918   0.0144
  -9.000  -0.6485   0.02264   0.01870  -0.0684   0.9896   0.0150
  -8.750  -0.6162   0.02289   0.01900  -0.0693   0.9877   0.0155
  -8.500  -0.5845   0.02261   0.01865  -0.0705   0.9860   0.0162
  -8.250  -0.5582   0.02133   0.01713  -0.0710   0.9825   0.0172
  -8.000  -0.5318   0.01960   0.01506  -0.0716   0.9790   0.0183
  -7.750  -0.5022   0.01852   0.01375  -0.0726   0.9767   0.0191
  -7.500  -0.4712   0.01818   0.01339  -0.0735   0.9745   0.0197
  -7.250  -0.4436   0.01798   0.01315  -0.0736   0.9701   0.0204
  -7.000  -0.4135   0.01751   0.01260  -0.0743   0.9671   0.0212
  -6.750  -0.3822   0.01689   0.01184  -0.0753   0.9648   0.0223
  -6.500  -0.3525   0.01629   0.01110  -0.0758   0.9614   0.0233
  -6.250  -0.3241   0.01573   0.01041  -0.0760   0.9567   0.0241
  -6.000  -0.2927   0.01526   0.00980  -0.0768   0.9533   0.0246
  -5.750  -0.2619   0.01398   0.00832  -0.0778   0.9504   0.0258
  -5.500  -0.2348   0.01329   0.00756  -0.0777   0.9444   0.0266
  -5.250  -0.2040   0.01275   0.00695  -0.0784   0.9399   0.0274
  -5.000  -0.1714   0.01230   0.00642  -0.0794   0.9361   0.0283
  -4.750  -0.1429   0.01183   0.00589  -0.0795   0.9295   0.0290
  -4.500  -0.1124   0.01136   0.00534  -0.0800   0.9239   0.0295
  -4.250  -0.0824   0.01092   0.00482  -0.0803   0.9177   0.0301
  -4.000  -0.0532   0.01053   0.00435  -0.0804   0.9083   0.0307
  -3.750  -0.0246   0.01021   0.00395  -0.0804   0.8954   0.0313
  -3.500   0.0032   0.00995   0.00360  -0.0802   0.8804   0.0320
  -3.250   0.0302   0.00970   0.00328  -0.0798   0.8661   0.0325
  -3.000   0.0568   0.00949   0.00299  -0.0793   0.8513   0.0329
  -2.750   0.0830   0.00926   0.00267  -0.0787   0.8342   0.0334
  -2.500   0.1089   0.00905   0.00235  -0.0781   0.8138   0.0343
  -2.250   0.1347   0.00890   0.00211  -0.0774   0.7927   0.0354
  -2.000   0.1606   0.00880   0.00191  -0.0767   0.7734   0.0365
  -1.750   0.1864   0.00874   0.00175  -0.0761   0.7545   0.0378
  -1.500   0.2122   0.00869   0.00162  -0.0755   0.7365   0.0394
  -1.250   0.2380   0.00866   0.00151  -0.0749   0.7191   0.0420
  -1.000   0.2637   0.00859   0.00143  -0.0742   0.7021   0.0523
  -0.750   0.2891   0.00849   0.00139  -0.0736   0.6854   0.0856
  -0.500   0.3147   0.00846   0.00135  -0.0730   0.6676   0.1070
  -0.250   0.3402   0.00844   0.00133  -0.0724   0.6483   0.1294
   0.000   0.3656   0.00845   0.00131  -0.0718   0.6262   0.1486
   0.250   0.3906   0.00844   0.00130  -0.0711   0.6019   0.1778
   0.500   0.4147   0.00837   0.00133  -0.0703   0.5744   0.2483
   0.750   0.4382   0.00833   0.00139  -0.0695   0.5391   0.3279
   1.000   0.4606   0.00840   0.00145  -0.0684   0.4913   0.3982
   1.250   0.4696   0.00734   0.00160  -0.0645   0.4553   0.8465
   1.750   0.5742   0.00780   0.00186  -0.0753   0.3862   1.0000
   2.000   0.5976   0.00801   0.00195  -0.0743   0.3665   1.0000
   2.250   0.6212   0.00821   0.00205  -0.0733   0.3489   1.0000
   2.500   0.6451   0.00838   0.00215  -0.0724   0.3350   1.0000
   2.750   0.6692   0.00855   0.00225  -0.0716   0.3227   1.0000
   3.000   0.6933   0.00872   0.00237  -0.0708   0.3115   1.0000
   3.250   0.7173   0.00891   0.00250  -0.0699   0.3009   1.0000
   3.500   0.7417   0.00907   0.00263  -0.0691   0.2903   1.0000
   3.750   0.7659   0.00925   0.00276  -0.0683   0.2798   1.0000
   4.000   0.7900   0.00945   0.00292  -0.0675   0.2697   1.0000
   4.250   0.8144   0.00963   0.00308  -0.0668   0.2607   1.0000
   4.500   0.8388   0.00982   0.00324  -0.0660   0.2523   1.0000
   4.750   0.8627   0.01005   0.00343  -0.0652   0.2412   1.0000
   5.000   0.8868   0.01027   0.00361  -0.0645   0.2298   1.0000
   5.250   0.9109   0.01049   0.00381  -0.0637   0.2198   1.0000
   5.500   0.9348   0.01074   0.00403  -0.0630   0.2099   1.0000
   5.750   0.9587   0.01098   0.00425  -0.0622   0.2001   1.0000
   6.000   0.9828   0.01121   0.00448  -0.0615   0.1918   1.0000
   6.500   1.0304   0.01172   0.00499  -0.0600   0.1749   1.0000
   6.750   1.0538   0.01202   0.00526  -0.0592   0.1637   1.0000
   7.000   1.0768   0.01234   0.00554  -0.0583   0.1518   1.0000
   7.250   1.0991   0.01273   0.00586  -0.0574   0.1336   1.0000
   7.500   1.1202   0.01323   0.00626  -0.0563   0.1097   1.0000
   7.750   1.1397   0.01389   0.00676  -0.0551   0.0832   1.0000
   8.250   1.1797   0.01508   0.00781  -0.0526   0.0549   1.0000
   8.500   1.2007   0.01556   0.00830  -0.0515   0.0471   1.0000
   8.750   1.2206   0.01613   0.00886  -0.0503   0.0380   1.0000
   9.000   1.2386   0.01686   0.00951  -0.0489   0.0253   1.0000
   9.250   1.2564   0.01757   0.01019  -0.0474   0.0181   1.0000
   9.500   1.2744   0.01825   0.01088  -0.0459   0.0152   1.0000
   9.750   1.2930   0.01882   0.01153  -0.0444   0.0138   1.0000
  10.000   1.3105   0.01946   0.01225  -0.0429   0.0126   1.0000
  10.250   1.3262   0.02020   0.01305  -0.0411   0.0114   1.0000
  10.500   1.3408   0.02096   0.01389  -0.0392   0.0105   1.0000
  10.750   1.3547   0.02161   0.01463  -0.0371   0.0101   1.0000
  11.000   1.3667   0.02234   0.01544  -0.0347   0.0096   1.0000
  11.250   1.3777   0.02312   0.01630  -0.0323   0.0091   1.0000
  11.500   1.3876   0.02397   0.01723  -0.0298   0.0087   1.0000
  11.750   1.3957   0.02495   0.01832  -0.0273   0.0084   1.0000
  12.000   1.3998   0.02622   0.01968  -0.0245   0.0080   1.0000
  12.250   1.4031   0.02757   0.02114  -0.0218   0.0078   1.0000
  12.500   1.4099   0.02875   0.02242  -0.0198   0.0076   1.0000
  12.750   1.4149   0.03010   0.02389  -0.0178   0.0074   1.0000
  13.000   1.4183   0.03165   0.02555  -0.0159   0.0071   1.0000
  13.250   1.4212   0.03334   0.02735  -0.0142   0.0069   1.0000
  13.500   1.4237   0.03517   0.02928  -0.0129   0.0066   1.0000
  13.750   1.4247   0.03725   0.03148  -0.0118   0.0064   1.0000
  14.000   1.4218   0.03988   0.03423  -0.0109   0.0064   1.0000
  14.250   1.4193   0.04268   0.03715  -0.0105   0.0063   1.0000
  14.500   1.4153   0.04584   0.04043  -0.0106   0.0061   1.0000
  14.750   1.4089   0.04953   0.04426  -0.0111   0.0060   1.0000
  15.000   1.4008   0.05367   0.04854  -0.0120   0.0060   1.0000
  15.250   1.3879   0.05880   0.05381  -0.0137   0.0058   1.0000
  15.500   1.3769   0.06401   0.05916  -0.0157   0.0059   1.0000
  15.750   1.3618   0.07019   0.06548  -0.0185   0.0057   1.0000
  16.000   1.3465   0.07668   0.07211  -0.0215   0.0057   1.0000
  16.250   1.3321   0.08314   0.07870  -0.0245   0.0057   1.0000
  16.500   1.3148   0.09017   0.08587  -0.0279   0.0057   1.0000
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