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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 500,000
Max Cl/Cd: 94.71 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe408-il-500000-n5.txt
Download as CSV file: xf-goe408-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4100   0.09435   0.09217  -0.0182   1.0000   0.0073
  -8.250  -0.4128   0.09137   0.08922  -0.0184   1.0000   0.0075
  -8.000  -0.4204   0.08827   0.08616  -0.0182   1.0000   0.0074
  -7.750  -0.4134   0.08412   0.08202  -0.0227   0.9974   0.0077
  -7.500  -0.4001   0.07817   0.07607  -0.0298   0.9940   0.0085
  -7.250  -0.3856   0.07030   0.06815  -0.0389   0.9894   0.0088
  -7.000  -0.3743   0.05929   0.05703  -0.0498   0.9837   0.0091
  -6.750  -0.3548   0.05119   0.04877  -0.0574   0.9791   0.0098
  -6.500  -0.3388   0.04590   0.04333  -0.0599   0.9729   0.0102
  -6.250  -0.3174   0.03983   0.03701  -0.0632   0.9685   0.0111
  -6.000  -0.3409   0.02555   0.02170  -0.0577   0.9509   0.0123
  -5.750  -0.3451   0.01795   0.01317  -0.0521   0.9388   0.0132
  -5.500  -0.3225   0.01619   0.01124  -0.0512   0.9317   0.0155
  -5.000  -0.2623   0.01643   0.01159  -0.0519   0.9140   0.0202
  -4.750  -0.2320   0.01408   0.00880  -0.0525   0.9054   0.0248
  -4.500  -0.1821   0.01520   0.01009  -0.0571   0.8946   0.0264
  -4.250  -0.1368   0.01366   0.00813  -0.0609   0.8852   0.0305
  -4.000  -0.0828   0.01352   0.00789  -0.0668   0.8725   0.0320
  -3.750  -0.0267   0.01394   0.00830  -0.0733   0.8538   0.0337
  -3.500   0.0226   0.01361   0.00773  -0.0782   0.8301   0.0360
  -3.250   0.0619   0.01301   0.00681  -0.0808   0.8048   0.0374
  -3.000   0.0918   0.01277   0.00632  -0.0811   0.7797   0.0382
  -2.750   0.1168   0.01207   0.00540  -0.0805   0.7595   0.0390
  -2.500   0.1413   0.01168   0.00488  -0.0798   0.7420   0.0397
  -2.250   0.1656   0.01144   0.00453  -0.0790   0.7268   0.0403
  -2.000   0.1900   0.01122   0.00422  -0.0781   0.7135   0.0410
  -1.750   0.2145   0.01099   0.00389  -0.0773   0.7019   0.0415
  -1.500   0.2388   0.01077   0.00358  -0.0765   0.6907   0.0420
  -1.250   0.2631   0.01059   0.00334  -0.0756   0.6792   0.0427
  -1.000   0.2871   0.01041   0.00310  -0.0747   0.6680   0.0432
  -0.750   0.3108   0.01023   0.00285  -0.0737   0.6571   0.0438
  -0.250   0.3584   0.01002   0.00255  -0.0717   0.6357   0.0456
   0.000   0.3819   0.00992   0.00240  -0.0707   0.6249   0.0464
   0.250   0.4052   0.00984   0.00228  -0.0696   0.6136   0.0469
   0.500   0.4283   0.00978   0.00217  -0.0685   0.6015   0.0473
   0.750   0.4513   0.00966   0.00202  -0.0674   0.5898   0.0484
   1.000   0.4739   0.00958   0.00189  -0.0661   0.5762   0.0496
   1.250   0.4964   0.00956   0.00183  -0.0649   0.5600   0.0512
   1.500   0.5181   0.00959   0.00179  -0.0635   0.5407   0.0527
   1.750   0.5404   0.00965   0.00178  -0.0622   0.5199   0.0537
   2.000   0.5625   0.00972   0.00177  -0.0609   0.4998   0.0554
   2.250   0.5847   0.00983   0.00180  -0.0597   0.4801   0.0573
   2.500   0.6072   0.00993   0.00183  -0.0585   0.4612   0.0592
   2.750   0.6298   0.01003   0.00188  -0.0574   0.4436   0.0643
   3.000   0.6526   0.01014   0.00197  -0.0563   0.4276   0.0696
   3.250   0.6760   0.01018   0.00208  -0.0554   0.4162   0.1143
   3.750   0.9272   0.00979   0.00339  -0.1023   0.3568   1.0000
   4.000   0.9488   0.01007   0.00354  -0.1010   0.3312   1.0000
   4.250   0.9714   0.01029   0.00370  -0.0999   0.3133   1.0000
   4.500   0.9934   0.01054   0.00389  -0.0988   0.2926   1.0000
   4.750   1.0147   0.01085   0.00411  -0.0975   0.2687   1.0000
   5.000   1.0352   0.01122   0.00436  -0.0960   0.2413   1.0000
   5.250   1.0547   0.01166   0.00465  -0.0944   0.2104   1.0000
   5.500   1.0748   0.01205   0.00495  -0.0929   0.1879   1.0000
   5.750   1.0947   0.01243   0.00527  -0.0914   0.1701   1.0000
   6.000   1.1143   0.01285   0.00561  -0.0899   0.1510   1.0000
   6.250   1.1344   0.01321   0.00593  -0.0884   0.1384   1.0000
   6.500   1.1539   0.01360   0.00628  -0.0868   0.1241   1.0000
   6.750   1.1726   0.01404   0.00666  -0.0851   0.1061   1.0000
   7.000   1.1909   0.01450   0.00705  -0.0834   0.0857   1.0000
   7.250   1.2041   0.01530   0.00764  -0.0807   0.0549   1.0000
   7.500   1.2217   0.01578   0.00814  -0.0788   0.0456   1.0000
   7.750   1.2386   0.01629   0.00865  -0.0768   0.0378   1.0000
   8.000   1.2549   0.01682   0.00917  -0.0746   0.0281   1.0000
   8.250   1.2682   0.01753   0.00981  -0.0720   0.0169   1.0000
   8.500   1.2837   0.01808   0.01040  -0.0697   0.0136   1.0000
   8.750   1.2972   0.01865   0.01103  -0.0671   0.0118   1.0000
   9.000   1.3085   0.01925   0.01168  -0.0640   0.0106   1.0000
   9.250   1.3197   0.01983   0.01234  -0.0609   0.0098   1.0000
   9.500   1.3306   0.02044   0.01304  -0.0578   0.0092   1.0000
   9.750   1.3422   0.02100   0.01368  -0.0550   0.0084   1.0000
  10.000   1.3521   0.02169   0.01445  -0.0520   0.0080   1.0000
  10.250   1.3596   0.02254   0.01538  -0.0486   0.0073   1.0000
  10.500   1.3652   0.02352   0.01646  -0.0450   0.0070   1.0000
  10.750   1.3739   0.02432   0.01736  -0.0421   0.0067   1.0000
  11.000   1.3810   0.02525   0.01840  -0.0391   0.0064   1.0000
  11.250   1.3867   0.02629   0.01954  -0.0360   0.0062   1.0000
  11.500   1.3930   0.02733   0.02068  -0.0332   0.0060   1.0000
  11.750   1.3957   0.02866   0.02212  -0.0301   0.0058   1.0000
  12.000   1.3992   0.03000   0.02356  -0.0274   0.0056   1.0000
  12.250   1.4024   0.03146   0.02511  -0.0251   0.0054   1.0000
  12.500   1.4025   0.03327   0.02702  -0.0227   0.0052   1.0000
  12.750   1.4020   0.03525   0.02912  -0.0207   0.0049   1.0000
  13.000   1.4009   0.03745   0.03142  -0.0191   0.0047   1.0000
  13.250   1.3952   0.04030   0.03440  -0.0177   0.0047   1.0000
  13.500   1.3957   0.04268   0.03691  -0.0168   0.0046   1.0000
  13.750   1.3942   0.04540   0.03978  -0.0161   0.0045   1.0000
  14.000   1.3902   0.04854   0.04306  -0.0157   0.0043   1.0000
  14.250   1.3875   0.05162   0.04627  -0.0155   0.0042   1.0000
  14.500   1.3789   0.05556   0.05035  -0.0156   0.0043   1.0000
  14.750   1.3750   0.05905   0.05397  -0.0159   0.0041   1.0000
  15.000   1.3663   0.06326   0.05831  -0.0165   0.0041   1.0000
  15.250   1.3568   0.06775   0.06294  -0.0173   0.0040   1.0000
  15.500   1.3482   0.07226   0.06759  -0.0184   0.0039   1.0000
  15.750   1.3365   0.07732   0.07278  -0.0196   0.0041   1.0000
  16.000   1.3268   0.08227   0.07786  -0.0211   0.0040   1.0000
  16.250   1.3158   0.08764   0.08336  -0.0229   0.0038   1.0000
  16.500   1.3105   0.09221   0.08804  -0.0246   0.0037   1.0000
  16.750   1.2928   0.09875   0.09474  -0.0268   0.0038   1.0000
  17.000   1.2827   0.10426   0.10036  -0.0289   0.0038   1.0000
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