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GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 389 AIRFOIL (goe389-il)
Reynolds number: 100,000
Max Cl/Cd: 56.19 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe389-il-100000-n5.txt
Download as CSV file: xf-goe389-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2615   0.09855   0.09396  -0.0370   1.0000   0.0651
  -9.250  -0.2748   0.09570   0.09119  -0.0392   1.0000   0.0663
  -8.250  -0.3799   0.08698   0.08234  -0.0401   1.0000   0.0433
  -8.000  -0.3812   0.08419   0.07962  -0.0388   1.0000   0.0429
  -7.750  -0.3856   0.08120   0.07670  -0.0386   1.0000   0.0425
  -7.500  -0.3925   0.07815   0.07373  -0.0386   1.0000   0.0422
  -7.250  -0.4004   0.07499   0.07063  -0.0386   1.0000   0.0419
  -7.000  -0.4032   0.07067   0.06632  -0.0410   0.9987   0.0419
  -6.750  -0.3758   0.05885   0.05415  -0.0566   0.9889   0.0431
  -6.500  -0.3511   0.05035   0.04516  -0.0651   0.9807   0.0435
  -6.250  -0.3249   0.04422   0.03863  -0.0705   0.9744   0.0441
  -6.000  -0.2981   0.04290   0.03734  -0.0722   0.9675   0.0461
  -5.750  -0.2669   0.03956   0.03368  -0.0757   0.9615   0.0483
  -5.500  -0.2362   0.03511   0.02865  -0.0790   0.9538   0.0489
  -5.250  -0.2017   0.03154   0.02447  -0.0820   0.9471   0.0497
  -5.000  -0.1655   0.02897   0.02132  -0.0845   0.9393   0.0524
  -4.750  -0.1296   0.02672   0.01852  -0.0864   0.9310   0.0536
  -4.500  -0.0929   0.02482   0.01617  -0.0882   0.9229   0.0542
  -4.250  -0.0597   0.02341   0.01437  -0.0891   0.9133   0.0549
  -4.000  -0.0245   0.02191   0.01274  -0.0906   0.9066   0.0561
  -3.750   0.0049   0.02096   0.01170  -0.0909   0.8968   0.0575
  -3.500   0.0380   0.02021   0.01084  -0.0919   0.8898   0.0607
  -3.250   0.0671   0.01955   0.01005  -0.0920   0.8799   0.0636
  -3.000   0.0965   0.01885   0.00924  -0.0921   0.8703   0.0654
  -2.750   0.1274   0.01817   0.00847  -0.0924   0.8620   0.0672
  -2.500   0.1539   0.01755   0.00786  -0.0921   0.8507   0.0702
  -2.250   0.1815   0.01707   0.00733  -0.0919   0.8398   0.0746
  -2.000   0.2100   0.01660   0.00677  -0.0917   0.8292   0.0815
  -1.750   0.2384   0.01608   0.00626  -0.0916   0.8186   0.0955
  -1.500   0.2651   0.01551   0.00596  -0.0913   0.8063   0.1449
  -1.250   0.2919   0.01491   0.00579  -0.0912   0.7941   0.2754
  -1.000   0.3180   0.01421   0.00567  -0.0909   0.7820   0.4350
  -0.750   0.3409   0.01289   0.00565  -0.0884   0.7707   0.8508
  -0.500   0.3851   0.01275   0.00530  -0.0913   0.7573   1.0000
  -0.250   0.4125   0.01280   0.00513  -0.0909   0.7437   1.0000
   0.000   0.4394   0.01288   0.00500  -0.0904   0.7293   1.0000
   0.250   0.4660   0.01298   0.00491  -0.0899   0.7143   1.0000
   0.500   0.4924   0.01310   0.00486  -0.0894   0.6987   1.0000
   0.750   0.5183   0.01323   0.00485  -0.0889   0.6818   1.0000
   1.000   0.5439   0.01337   0.00486  -0.0883   0.6637   1.0000
   1.250   0.5695   0.01351   0.00488  -0.0877   0.6448   1.0000
   1.500   0.5952   0.01366   0.00490  -0.0871   0.6256   1.0000
   1.750   0.6208   0.01381   0.00493  -0.0865   0.6057   1.0000
   2.000   0.6464   0.01399   0.00497  -0.0860   0.5867   1.0000
   2.250   0.6720   0.01419   0.00504  -0.0854   0.5695   1.0000
   2.500   0.6977   0.01443   0.00513  -0.0849   0.5541   1.0000
   2.750   0.7234   0.01468   0.00527  -0.0844   0.5402   1.0000
   3.000   0.7492   0.01496   0.00546  -0.0840   0.5278   1.0000
   3.250   0.7750   0.01526   0.00566  -0.0836   0.5169   1.0000
   3.500   0.8008   0.01558   0.00590  -0.0832   0.5067   1.0000
   3.750   0.8266   0.01589   0.00620  -0.0828   0.4966   1.0000
   4.000   0.8521   0.01623   0.00648  -0.0824   0.4869   1.0000
   4.250   0.8775   0.01658   0.00678  -0.0820   0.4766   1.0000
   4.500   0.9028   0.01691   0.00714  -0.0816   0.4663   1.0000
   4.750   0.9281   0.01727   0.00747  -0.0811   0.4573   1.0000
   5.000   0.9533   0.01761   0.00784  -0.0807   0.4480   1.0000
   5.250   0.9786   0.01798   0.00826  -0.0803   0.4402   1.0000
   5.500   1.0038   0.01834   0.00867  -0.0799   0.4322   1.0000
   5.750   1.0288   0.01871   0.00910  -0.0795   0.4244   1.0000
   6.000   1.0536   0.01908   0.00954  -0.0790   0.4165   1.0000
   6.250   1.0785   0.01947   0.01005  -0.0786   0.4093   1.0000
   6.500   1.1028   0.01985   0.01052  -0.0780   0.4011   1.0000
   6.750   1.1257   0.02019   0.01098  -0.0773   0.3896   1.0000
   7.000   1.1462   0.02047   0.01131  -0.0760   0.3720   1.0000
   7.250   1.1653   0.02075   0.01165  -0.0746   0.3497   1.0000
   7.500   1.1850   0.02109   0.01206  -0.0734   0.3285   1.0000
   7.750   1.2044   0.02151   0.01252  -0.0721   0.3067   1.0000
   8.000   1.2239   0.02199   0.01306  -0.0709   0.2844   1.0000
   8.250   1.2411   0.02261   0.01365  -0.0694   0.2547   1.0000
   8.500   1.2515   0.02371   0.01447  -0.0671   0.1996   1.0000
   8.750   1.2589   0.02519   0.01562  -0.0647   0.1501   1.0000
   9.000   1.2673   0.02662   0.01690  -0.0624   0.1261   1.0000
   9.250   1.2759   0.02797   0.01823  -0.0601   0.1078   1.0000
   9.500   1.2787   0.02956   0.01969  -0.0571   0.0658   1.0000
   9.750   1.2760   0.03156   0.02149  -0.0537   0.0447   1.0000
  10.000   1.2763   0.03342   0.02335  -0.0510   0.0305   1.0000
  10.250   1.2772   0.03532   0.02530  -0.0487   0.0266   1.0000
  10.500   1.2779   0.03735   0.02741  -0.0466   0.0247   1.0000
  10.750   1.2788   0.03949   0.02973  -0.0449   0.0236   1.0000
  11.000   1.2786   0.04184   0.03225  -0.0434   0.0228   1.0000
  11.250   1.2769   0.04449   0.03506  -0.0423   0.0220   1.0000
  11.500   1.2735   0.04747   0.03821  -0.0415   0.0212   1.0000
  11.750   1.2684   0.05080   0.04170  -0.0410   0.0206   1.0000
  12.000   1.2611   0.05454   0.04559  -0.0408   0.0200   1.0000
  12.250   1.2525   0.05862   0.04983  -0.0410   0.0195   1.0000
  12.500   1.2444   0.06279   0.05414  -0.0414   0.0191   1.0000
  12.750   1.2384   0.06683   0.05836  -0.0419   0.0188   1.0000
  13.000   1.2322   0.07101   0.06271  -0.0426   0.0186   1.0000
  13.250   1.2261   0.07525   0.06711  -0.0433   0.0183   1.0000
  13.500   1.2206   0.07944   0.07146  -0.0441   0.0182   1.0000
  13.750   1.2162   0.08353   0.07569  -0.0448   0.0180   1.0000
  14.000   1.2128   0.08745   0.07974  -0.0455   0.0178   1.0000
  14.250   1.2106   0.09117   0.08359  -0.0460   0.0176   1.0000
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