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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 200,000
Max Cl/Cd: 80.96 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe400-il-200000.txt
Download as CSV file: xf-goe400-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3871   0.10001   0.09659  -0.0015   1.0000   0.0410
  -7.750  -0.3803   0.09726   0.09388  -0.0041   1.0000   0.0430
  -7.500  -0.3745   0.09583   0.09251  -0.0122   1.0000   0.0443
  -7.250  -0.3576   0.09285   0.08953  -0.0216   1.0000   0.0446
  -7.000  -0.3514   0.08717   0.08388  -0.0210   1.0000   0.0453
  -6.750  -0.3429   0.08341   0.08015  -0.0173   1.0000   0.0462
  -6.500  -0.3306   0.08039   0.07714  -0.0177   1.0000   0.0474
  -6.250  -0.3164   0.07749   0.07426  -0.0197   1.0000   0.0496
  -6.000  -0.2986   0.07437   0.07115  -0.0241   1.0000   0.0532
  -5.750  -0.2594   0.07025   0.06692  -0.0410   1.0000   0.0558
  -5.500  -0.2575   0.06650   0.06326  -0.0371   1.0000   0.0566
  -5.250  -0.2513   0.06408   0.06091  -0.0348   1.0000   0.0576
  -5.000  -0.2469   0.06220   0.05908  -0.0335   0.9996   0.0589
  -4.500  -0.1442   0.05243   0.04904  -0.0549   0.9817   0.0688
  -4.250  -0.1064   0.04920   0.04577  -0.0594   0.9698   0.0721
  -4.000  -0.0439   0.04434   0.04051  -0.0719   0.9541   0.0793
  -3.750  -0.0197   0.04172   0.03793  -0.0724   0.9340   0.0814
  -3.500   0.0102   0.03944   0.03555  -0.0742   0.9125   0.0854
  -3.250   0.0551   0.03616   0.03172  -0.0796   0.8910   0.0916
  -3.000   0.0754   0.03374   0.02925  -0.0790   0.8699   0.0928
  -2.750   0.0986   0.03185   0.02723  -0.0788   0.8511   0.0945
  -2.500   0.1248   0.03011   0.02529  -0.0790   0.8339   0.0979
  -2.250   0.1713   0.02053   0.01426  -0.0827   0.8220   0.0671
  -2.000   0.1985   0.01834   0.01166  -0.0825   0.8073   0.0664
  -1.750   0.2261   0.01648   0.00933  -0.0823   0.7934   0.0666
  -1.500   0.2533   0.01520   0.00776  -0.0819   0.7800   0.0682
  -1.250   0.2800   0.01512   0.00762  -0.0814   0.7670   0.0716
  -1.000   0.3073   0.01449   0.00677  -0.0809   0.7551   0.0750
  -0.750   0.3348   0.01379   0.00579  -0.0803   0.7441   0.0789
  -0.500   0.3620   0.01363   0.00563  -0.0800   0.7319   0.0845
  -0.250   0.3895   0.01338   0.00529  -0.0795   0.7207   0.0952
   0.000   0.4168   0.01331   0.00510  -0.0791   0.7103   0.1182
   0.250   0.4436   0.01313   0.00494  -0.0788   0.6998   0.1368
   0.500   0.4707   0.01303   0.00480  -0.0785   0.6888   0.1483
   0.750   0.4978   0.01305   0.00477  -0.0781   0.6786   0.1591
   1.000   0.5246   0.01306   0.00477  -0.0778   0.6688   0.1738
   1.250   0.5517   0.01290   0.00467  -0.0775   0.6578   0.1811
   1.500   0.5788   0.01282   0.00457  -0.0771   0.6476   0.1849
   1.750   0.6059   0.01280   0.00448  -0.0767   0.6381   0.1892
   2.000   0.6329   0.01266   0.00443  -0.0764   0.6269   0.1927
   2.250   0.6598   0.01260   0.00440  -0.0760   0.6157   0.1972
   2.500   0.6866   0.01258   0.00436  -0.0756   0.6041   0.2028
   2.750   0.7133   0.01253   0.00432  -0.0751   0.5923   0.2105
   3.000   0.7401   0.01248   0.00435  -0.0747   0.5793   0.2245
   3.250   0.7661   0.01216   0.00444  -0.0743   0.5668   0.3623
   3.500   0.7947   0.01115   0.00442  -0.0740   0.5542   1.0000
   3.750   0.8214   0.01130   0.00449  -0.0736   0.5413   1.0000
   4.000   0.8480   0.01145   0.00458  -0.0731   0.5282   1.0000
   4.250   0.8745   0.01160   0.00468  -0.0727   0.5141   1.0000
   4.500   0.9008   0.01176   0.00480  -0.0722   0.4997   1.0000
   4.750   0.9272   0.01196   0.00498  -0.0718   0.4863   1.0000
   5.000   0.9535   0.01217   0.00516  -0.0714   0.4732   1.0000
   5.250   0.9797   0.01239   0.00538  -0.0710   0.4592   1.0000
   5.500   1.0056   0.01262   0.00561  -0.0705   0.4442   1.0000
   5.750   1.0314   0.01286   0.00588  -0.0701   0.4283   1.0000
   6.000   1.0572   0.01312   0.00617  -0.0696   0.4125   1.0000
   6.250   1.0827   0.01339   0.00648  -0.0691   0.3957   1.0000
   6.500   1.1076   0.01368   0.00676  -0.0686   0.3739   1.0000
   6.750   1.1319   0.01401   0.00707  -0.0680   0.3464   1.0000
   7.000   1.1555   0.01443   0.00743  -0.0674   0.3152   1.0000
   7.250   1.1786   0.01495   0.00786  -0.0668   0.2804   1.0000
   7.500   1.2007   0.01564   0.00840  -0.0661   0.2372   1.0000
   7.750   1.2211   0.01658   0.00914  -0.0653   0.1873   1.0000
   8.000   1.2396   0.01782   0.01008  -0.0644   0.1360   1.0000
   8.250   1.2545   0.01956   0.01144  -0.0632   0.0863   1.0000
   8.500   1.2693   0.02133   0.01298  -0.0617   0.0512   1.0000
   8.750   1.2855   0.02273   0.01435  -0.0603   0.0421   1.0000
   9.000   1.3019   0.02401   0.01576  -0.0589   0.0377   1.0000
   9.250   1.3154   0.02552   0.01732  -0.0574   0.0346   1.0000
   9.500   1.3224   0.02767   0.01952  -0.0551   0.0327   1.0000
   9.750   1.3355   0.02913   0.02112  -0.0533   0.0317   1.0000
  10.000   1.3470   0.03076   0.02286  -0.0515   0.0306   1.0000
  10.250   1.3579   0.03242   0.02463  -0.0496   0.0294   1.0000
  10.500   1.3671   0.03406   0.02635  -0.0476   0.0281   1.0000
  10.750   1.3753   0.03588   0.02824  -0.0457   0.0269   1.0000
  11.000   1.3855   0.03828   0.03068  -0.0440   0.0259   1.0000
  11.250   1.4021   0.04182   0.03436  -0.0428   0.0253   1.0000
  11.500   1.4110   0.04442   0.03719  -0.0410   0.0250   1.0000
  11.750   1.4160   0.04692   0.03994  -0.0392   0.0248   1.0000
  12.000   1.4179   0.04975   0.04304  -0.0373   0.0247   1.0000
  12.250   1.4163   0.05293   0.04648  -0.0356   0.0247   1.0000
  12.500   1.4112   0.05641   0.05023  -0.0342   0.0247   1.0000
  12.750   1.4028   0.06014   0.05423  -0.0333   0.0247   1.0000
  13.000   1.3918   0.06420   0.05854  -0.0329   0.0246   1.0000
  13.250   1.3786   0.06863   0.06322  -0.0332   0.0246   1.0000
  13.500   1.3635   0.07349   0.06834  -0.0342   0.0246   1.0000
  13.750   1.3469   0.07891   0.07399  -0.0357   0.0247   1.0000
  14.000   1.3287   0.08473   0.08002  -0.0378   0.0247   1.0000
  14.250   1.3092   0.09116   0.08662  -0.0405   0.0248   1.0000
  14.500   1.2886   0.09832   0.09395  -0.0433   0.0250   1.0000
  14.750   1.1329   0.09520   0.09099  -0.0280   0.0258   1.0000
  15.000   1.1029   0.10159   0.09760  -0.0311   0.0261   1.0000
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