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GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 439 AIRFOIL (goe439-il)
Reynolds number: 200,000
Max Cl/Cd: 79.29 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe439-il-200000.txt
Download as CSV file: xf-goe439-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 439 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3104   0.09090   0.08783  -0.0267   1.0000   0.0353
  -7.000  -0.3234   0.08997   0.08700  -0.0253   1.0000   0.0356
  -6.750  -0.3364   0.08906   0.08618  -0.0239   1.0000   0.0357
  -6.500  -0.3115   0.08536   0.08246  -0.0345   0.9953   0.0362
  -6.250  -0.2730   0.07997   0.07699  -0.0455   0.9886   0.0364
  -6.000  -0.2585   0.07283   0.06989  -0.0476   0.9845   0.0375
  -5.750  -0.2361   0.06903   0.06607  -0.0493   0.9786   0.0390
  -5.500  -0.2028   0.06474   0.06173  -0.0557   0.9727   0.0411
  -5.250  -0.1660   0.06009   0.05700  -0.0639   0.9654   0.0442
  -5.000  -0.0957   0.05429   0.05076  -0.0819   0.9583   0.0485
  -4.750  -0.0820   0.04915   0.04577  -0.0824   0.9522   0.0515
  -4.500  -0.0461   0.04573   0.04225  -0.0870   0.9462   0.0560
  -4.250   0.0080   0.03951   0.03559  -0.0972   0.9425   0.0633
  -4.000   0.0345   0.03704   0.03310  -0.0984   0.9332   0.0662
  -3.750   0.0785   0.03295   0.02858  -0.1037   0.9283   0.0766
  -3.500   0.1058   0.03083   0.02642  -0.1044   0.9180   0.0815
  -3.250   0.1380   0.02848   0.02385  -0.1061   0.9092   0.0944
  -3.000   0.1795   0.01889   0.01257  -0.1066   0.9017   0.0477
  -2.750   0.2084   0.01650   0.00970  -0.1066   0.8913   0.0505
  -2.500   0.2383   0.01552   0.00856  -0.1066   0.8812   0.0566
  -2.250   0.2692   0.01451   0.00722  -0.1065   0.8714   0.0616
  -2.000   0.2960   0.01369   0.00636  -0.1060   0.8589   0.0708
  -1.750   0.3230   0.01308   0.00567  -0.1054   0.8464   0.0793
  -1.500   0.3501   0.01270   0.00519  -0.1048   0.8338   0.0903
  -1.250   0.3768   0.01236   0.00481  -0.1042   0.8210   0.1048
  -1.000   0.4033   0.01201   0.00443  -0.1035   0.8081   0.1294
  -0.750   0.4290   0.01156   0.00407  -0.1029   0.7951   0.1648
  -0.500   0.4548   0.01133   0.00385  -0.1023   0.7818   0.1963
  -0.250   0.4805   0.01111   0.00368  -0.1017   0.7683   0.2310
   0.000   0.4999   0.00996   0.00368  -0.1002   0.7551   0.5939
   0.250   0.5459   0.00927   0.00346  -0.1033   0.7407   1.0000
   0.500   0.5714   0.00938   0.00338  -0.1025   0.7260   1.0000
   0.750   0.5968   0.00950   0.00334  -0.1018   0.7110   1.0000
   1.000   0.6222   0.00963   0.00333  -0.1011   0.6957   1.0000
   1.250   0.6475   0.00976   0.00333  -0.1004   0.6803   1.0000
   1.500   0.6728   0.00989   0.00334  -0.0997   0.6647   1.0000
   1.750   0.6980   0.01003   0.00337  -0.0990   0.6489   1.0000
   2.000   0.7233   0.01018   0.00341  -0.0983   0.6333   1.0000
   2.250   0.7485   0.01034   0.00347  -0.0976   0.6178   1.0000
   2.500   0.7737   0.01052   0.00355  -0.0970   0.6025   1.0000
   2.750   0.7988   0.01072   0.00364  -0.0964   0.5875   1.0000
   3.000   0.8240   0.01093   0.00377  -0.0957   0.5729   1.0000
   3.250   0.8490   0.01116   0.00394  -0.0951   0.5585   1.0000
   3.500   0.8741   0.01141   0.00412  -0.0946   0.5447   1.0000
   3.750   0.8991   0.01167   0.00433  -0.0940   0.5311   1.0000
   4.000   0.9239   0.01193   0.00455  -0.0934   0.5173   1.0000
   4.250   0.9486   0.01220   0.00481  -0.0928   0.5036   1.0000
   4.500   0.9733   0.01248   0.00507  -0.0922   0.4903   1.0000
   4.750   0.9980   0.01277   0.00535  -0.0916   0.4780   1.0000
   5.000   1.0226   0.01307   0.00564  -0.0910   0.4659   1.0000
   5.250   1.0466   0.01334   0.00594  -0.0903   0.4520   1.0000
   5.500   1.0701   0.01360   0.00620  -0.0895   0.4370   1.0000
   5.750   1.0933   0.01385   0.00648  -0.0886   0.4217   1.0000
   6.000   1.1157   0.01410   0.00672  -0.0876   0.4039   1.0000
   6.250   1.1377   0.01438   0.00701  -0.0866   0.3860   1.0000
   6.500   1.1592   0.01462   0.00729  -0.0855   0.3628   1.0000
   6.750   1.1797   0.01494   0.00760  -0.0842   0.3360   1.0000
   7.000   1.1984   0.01540   0.00796  -0.0827   0.2986   1.0000
   7.250   1.2092   0.01656   0.00861  -0.0802   0.2079   1.0000
   7.500   1.2034   0.01956   0.01050  -0.0758   0.0521   1.0000
   7.750   1.2159   0.02085   0.01177  -0.0734   0.0399   1.0000
   8.000   1.2282   0.02205   0.01313  -0.0710   0.0356   1.0000
   8.250   1.2334   0.02363   0.01488  -0.0677   0.0321   1.0000
   8.500   1.2414   0.02477   0.01617  -0.0648   0.0309   1.0000
   8.750   1.2449   0.02610   0.01762  -0.0612   0.0299   1.0000
   9.000   1.2472   0.02758   0.01922  -0.0578   0.0290   1.0000
   9.250   1.2496   0.02921   0.02095  -0.0547   0.0283   1.0000
   9.500   1.2528   0.03098   0.02280  -0.0519   0.0276   1.0000
   9.750   1.2580   0.03278   0.02470  -0.0496   0.0267   1.0000
  10.000   1.2641   0.03476   0.02672  -0.0476   0.0253   1.0000
  10.250   1.2764   0.03703   0.02898  -0.0460   0.0240   1.0000
  10.500   1.3047   0.03954   0.03153  -0.0456   0.0236   1.0000
  10.750   1.3369   0.04226   0.03440  -0.0459   0.0236   1.0000
  11.000   1.3562   0.04441   0.03679  -0.0448   0.0240   1.0000
  11.250   1.3712   0.04687   0.03971  -0.0428   0.0260   1.0000
  11.500   1.3828   0.05072   0.04400  -0.0409   0.0278   1.0000
  11.750   1.3852   0.05420   0.04783  -0.0388   0.0285   1.0000
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