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GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 645 AIRFOIL (goe645-il)
Reynolds number: 200,000
Max Cl/Cd: 66.31 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe645-il-200000.txt
Download as CSV file: xf-goe645-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 645 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6730   0.05019   0.04589  -0.0839   1.0000   0.0508
 -11.250  -0.7005   0.04759   0.04316  -0.0807   1.0000   0.0507
 -11.000  -0.7271   0.04549   0.04093  -0.0765   1.0000   0.0507
 -10.750  -0.7442   0.04284   0.03810  -0.0739   0.9988   0.0509
 -10.500  -0.7134   0.03944   0.03464  -0.0782   0.9932   0.0523
 -10.250  -0.6806   0.03723   0.03234  -0.0817   0.9861   0.0537
 -10.000  -0.6511   0.03423   0.02899  -0.0854   0.9785   0.0550
  -9.750  -0.6209   0.03142   0.02575  -0.0885   0.9706   0.0563
  -9.500  -0.5915   0.02943   0.02329  -0.0906   0.9615   0.0576
  -9.250  -0.5561   0.02710   0.02093  -0.0933   0.9562   0.0595
  -9.000  -0.5231   0.02575   0.01951  -0.0949   0.9481   0.0611
  -8.750  -0.4859   0.02429   0.01787  -0.0972   0.9423   0.0630
  -8.500  -0.4474   0.02300   0.01633  -0.0995   0.9368   0.0652
  -8.250  -0.4152   0.02158   0.01491  -0.1007   0.9279   0.0675
  -8.000  -0.3748   0.02053   0.01384  -0.1032   0.9228   0.0702
  -7.750  -0.3449   0.01968   0.01287  -0.1036   0.9110   0.0729
  -7.500  -0.3112   0.01874   0.01191  -0.1047   0.9018   0.0762
  -7.250  -0.2788   0.01812   0.01125  -0.1055   0.8911   0.0803
  -7.000  -0.2505   0.01746   0.01051  -0.1054   0.8787   0.0848
  -6.750  -0.2205   0.01698   0.00999  -0.1056   0.8674   0.0909
  -6.500  -0.1933   0.01647   0.00943  -0.1052   0.8550   0.0995
  -6.250  -0.1689   0.01594   0.00889  -0.1044   0.8419   0.1126
  -6.000  -0.1431   0.01546   0.00831  -0.1038   0.8301   0.1327
  -5.750  -0.1173   0.01510   0.00796  -0.1033   0.8183   0.1501
  -5.500  -0.0922   0.01499   0.00777  -0.1025   0.8051   0.1634
  -5.250  -0.0658   0.01491   0.00763  -0.1019   0.7933   0.1746
  -5.000  -0.0390   0.01480   0.00746  -0.1013   0.7820   0.1841
  -4.750  -0.0135   0.01474   0.00728  -0.1005   0.7691   0.1939
  -4.500   0.0126   0.01470   0.00721  -0.0999   0.7572   0.2035
  -4.250   0.0392   0.01464   0.00706  -0.0993   0.7456   0.2139
  -4.000   0.0648   0.01464   0.00696  -0.0985   0.7328   0.2254
  -3.750   0.0909   0.01462   0.00695  -0.0978   0.7212   0.2367
  -3.500   0.1172   0.01463   0.00689  -0.0971   0.7097   0.2498
  -3.250   0.1425   0.01464   0.00686  -0.0963   0.6968   0.2637
  -3.000   0.1688   0.01473   0.00680  -0.0956   0.6854   0.2773
  -2.750   0.1949   0.01465   0.00673  -0.0950   0.6742   0.2883
  -2.500   0.2206   0.01460   0.00662  -0.0943   0.6622   0.2991
  -2.250   0.2471   0.01461   0.00653  -0.0937   0.6516   0.3092
  -2.000   0.2731   0.01453   0.00641  -0.0931   0.6403   0.3182
  -1.750   0.2993   0.01453   0.00635  -0.0925   0.6295   0.3273
  -1.500   0.3261   0.01448   0.00619  -0.0920   0.6198   0.3357
  -1.250   0.3516   0.01444   0.00614  -0.0913   0.6081   0.3440
  -1.000   0.3778   0.01441   0.00600  -0.0907   0.5974   0.3522
  -0.750   0.4037   0.01435   0.00590  -0.0901   0.5863   0.3603
  -0.500   0.4294   0.01434   0.00583  -0.0894   0.5752   0.3692
  -0.250   0.4560   0.01434   0.00577  -0.0890   0.5666   0.3787
   0.000   0.4814   0.01432   0.00578  -0.0883   0.5571   0.3894
   0.500   0.5336   0.01432   0.00578  -0.0873   0.5406   0.4106
   0.750   0.5603   0.01437   0.00575  -0.0869   0.5332   0.4232
   1.000   0.5854   0.01435   0.00583  -0.0863   0.5251   0.4376
   1.250   0.6109   0.01433   0.00583  -0.0856   0.5170   0.4547
   1.500   0.6357   0.01432   0.00590  -0.0849   0.5086   0.4757
   1.750   0.6600   0.01424   0.00594  -0.0841   0.5003   0.5045
   2.000   0.6832   0.01412   0.00603  -0.0831   0.4924   0.5584
   2.250   0.7586   0.01333   0.00614  -0.0924   0.4812   1.0000
   2.500   0.7821   0.01351   0.00625  -0.0914   0.4736   1.0000
   2.750   0.8059   0.01369   0.00634  -0.0905   0.4663   1.0000
   3.000   0.8300   0.01392   0.00646  -0.0897   0.4594   1.0000
   3.250   0.8530   0.01409   0.00660  -0.0886   0.4517   1.0000
   3.500   0.8777   0.01435   0.00670  -0.0879   0.4451   1.0000
   3.750   0.8999   0.01452   0.00690  -0.0868   0.4374   1.0000
   4.000   0.9235   0.01473   0.00703  -0.0859   0.4305   1.0000
   4.250   0.9467   0.01497   0.00724  -0.0849   0.4234   1.0000
   4.500   0.9693   0.01517   0.00742  -0.0839   0.4158   1.0000
   4.750   0.9927   0.01544   0.00759  -0.0830   0.4088   1.0000
   5.000   1.0142   0.01563   0.00781  -0.0817   0.4005   1.0000
   5.250   1.0378   0.01592   0.00797  -0.0809   0.3938   1.0000
   5.500   1.0589   0.01614   0.00826  -0.0796   0.3860   1.0000
   5.750   1.0812   0.01641   0.00847  -0.0786   0.3793   1.0000
   6.000   1.1029   0.01670   0.00876  -0.0775   0.3722   1.0000
   6.250   1.1242   0.01697   0.00902  -0.0763   0.3652   1.0000
   6.500   1.1467   0.01732   0.00929  -0.0754   0.3594   1.0000
   6.750   1.1670   0.01760   0.00965  -0.0741   0.3525   1.0000
   7.000   1.1883   0.01792   0.00992  -0.0730   0.3466   1.0000
   7.250   1.2095   0.01829   0.01027  -0.0719   0.3411   1.0000
   7.500   1.2291   0.01861   0.01065  -0.0705   0.3350   1.0000
   7.750   1.2494   0.01895   0.01093  -0.0693   0.3295   1.0000
   8.000   1.2684   0.01932   0.01133  -0.0679   0.3237   1.0000
   8.250   1.2868   0.01966   0.01173  -0.0663   0.3183   1.0000
   8.500   1.3063   0.02005   0.01208  -0.0651   0.3137   1.0000
   8.750   1.3253   0.02048   0.01252  -0.0637   0.3093   1.0000
   9.000   1.3419   0.02087   0.01300  -0.0619   0.3047   1.0000
   9.250   1.3580   0.02127   0.01342  -0.0601   0.3005   1.0000
   9.500   1.3768   0.02173   0.01383  -0.0588   0.2966   1.0000
   9.750   1.3906   0.02219   0.01438  -0.0567   0.2923   1.0000
  10.000   1.4030   0.02264   0.01492  -0.0544   0.2875   1.0000
  10.250   1.4176   0.02312   0.01541  -0.0526   0.2832   1.0000
  10.500   1.4351   0.02368   0.01592  -0.0513   0.2793   1.0000
  10.750   1.4453   0.02426   0.01665  -0.0489   0.2750   1.0000
  11.000   1.4568   0.02486   0.01734  -0.0469   0.2705   1.0000
  11.250   1.4706   0.02548   0.01794  -0.0453   0.2662   1.0000
  11.500   1.4817   0.02622   0.01874  -0.0434   0.2617   1.0000
  11.750   1.4893   0.02703   0.01968  -0.0413   0.2567   1.0000
  12.000   1.4988   0.02785   0.02052  -0.0395   0.2518   1.0000
  12.250   1.5078   0.02880   0.02149  -0.0377   0.2466   1.0000
  12.500   1.5114   0.02995   0.02279  -0.0357   0.2409   1.0000
  12.750   1.5182   0.03106   0.02386  -0.0340   0.2350   1.0000
  13.000   1.5203   0.03251   0.02543  -0.0322   0.2288   1.0000
  13.250   1.5213   0.03408   0.02706  -0.0306   0.2221   1.0000
  13.500   1.5246   0.03566   0.02864  -0.0293   0.2160   1.0000
  13.750   1.5231   0.03764   0.03075  -0.0280   0.2094   1.0000
  14.000   1.5268   0.03931   0.03233  -0.0269   0.2036   1.0000
  14.250   1.5247   0.04159   0.03479  -0.0260   0.1979   1.0000
  14.500   1.5250   0.04373   0.03698  -0.0252   0.1928   1.0000
  14.750   1.5296   0.04551   0.03871  -0.0244   0.1887   1.0000
  15.000   1.5284   0.04801   0.04139  -0.0240   0.1845   1.0000
  15.250   1.5285   0.05042   0.04390  -0.0236   0.1804   1.0000
  15.500   1.5313   0.05258   0.04607  -0.0233   0.1772   1.0000
  15.750   1.5352   0.05466   0.04816  -0.0230   0.1742   1.0000
  16.000   1.5343   0.05742   0.05109  -0.0230   0.1713   1.0000
  16.250   1.5330   0.06027   0.05406  -0.0231   0.1680   1.0000
  16.500   1.5326   0.06303   0.05688  -0.0233   0.1650   1.0000
  16.750   1.5352   0.06539   0.05919  -0.0234   0.1616   1.0000
  17.000   1.5297   0.06901   0.06300  -0.0240   0.1588   1.0000
  17.250   1.5243   0.07267   0.06679  -0.0248   0.1555   1.0000
  17.500   1.5216   0.07598   0.07015  -0.0255   0.1524   1.0000
  17.750   1.5252   0.07831   0.07241  -0.0257   0.1490   1.0000
  18.000   1.5165   0.08264   0.07694  -0.0269   0.1465   1.0000
  18.250   1.5090   0.08685   0.08129  -0.0282   0.1436   1.0000
  18.500   1.5050   0.09051   0.08503  -0.0292   0.1407   1.0000
  18.750   1.5102   0.09268   0.08712  -0.0296   0.1374   1.0000
  19.000   1.5047   0.09665   0.09123  -0.0308   0.1349   1.0000
  19.250   1.4958   0.10125   0.09599  -0.0324   0.1326   1.0000
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