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GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 439 AIRFOIL (goe439-il)
Reynolds number: 50,000
Max Cl/Cd: 28.7 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe439-il-50000.txt
Download as CSV file: xf-goe439-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2985   0.10429   0.09779  -0.0276   1.0000   0.1368
  -7.750  -0.3025   0.10276   0.09638  -0.0274   1.0000   0.1410
  -7.500  -0.3181   0.10284   0.09666  -0.0271   1.0000   0.1431
  -7.250  -0.3334   0.10334   0.09734  -0.0296   1.0000   0.1440
  -7.000  -0.3091   0.09588   0.08986  -0.0243   1.0000   0.1506
  -6.750  -0.3155   0.09443   0.08854  -0.0241   1.0000   0.1553
  -6.500  -0.3299   0.09473   0.08900  -0.0268   1.0000   0.1578
  -6.250  -0.3218   0.08983   0.08417  -0.0224   1.0000   0.1625
  -6.000  -0.3246   0.08793   0.08233  -0.0212   1.0000   0.1681
  -5.750  -0.3364   0.08851   0.08302  -0.0265   1.0000   0.1725
  -5.250  -0.3359   0.08347   0.07807  -0.0245   1.0000   0.1867
  -5.000  -0.3354   0.07947   0.07419  -0.0181   1.0000   0.1932
  -4.500  -0.3287   0.07574   0.07048  -0.0228   1.0000   0.2160
  -4.250  -0.3283   0.07245   0.06728  -0.0179   1.0000   0.2249
  -4.000  -0.3226   0.06990   0.06476  -0.0180   1.0000   0.2368
  -3.750  -0.3153   0.06735   0.06223  -0.0182   1.0000   0.2523
  -3.500  -0.3041   0.06493   0.05978  -0.0203   1.0000   0.2751
  -3.250  -0.2940   0.06268   0.05752  -0.0206   1.0000   0.3029
  -3.000  -0.2905   0.05985   0.05478  -0.0171   1.0000   0.3227
  -2.750  -0.2849   0.05761   0.05256  -0.0151   1.0000   0.3634
  -2.500  -0.2860   0.05547   0.05054  -0.0099   1.0000   0.4096
  -1.500  -0.0337   0.04015   0.03240  -0.0584   0.9921   0.1854
  -1.250   0.0277   0.03697   0.02843  -0.0649   0.9813   0.1653
  -1.000   0.0852   0.03519   0.02581  -0.0704   0.9694   0.1718
  -0.750   0.1360   0.03355   0.02377  -0.0748   0.9567   0.1813
  -0.500   0.1842   0.03254   0.02231  -0.0786   0.9431   0.2021
  -0.250   0.2336   0.03160   0.02113  -0.0824   0.9294   0.2365
   0.000   0.2824   0.03061   0.02017  -0.0859   0.9159   0.2995
   0.250   0.3290   0.02781   0.01939  -0.0888   0.9032   1.0000
   0.500   0.3750   0.02840   0.01907  -0.0918   0.8877   1.0000
   0.750   0.4182   0.02889   0.01916  -0.0946   0.8723   1.0000
   1.000   0.4615   0.02931   0.01929  -0.0973   0.8572   1.0000
   1.250   0.4950   0.02981   0.01958  -0.0984   0.8408   1.0000
   1.500   0.5299   0.03027   0.01988  -0.0997   0.8249   1.0000
   1.750   0.5663   0.03066   0.02014  -0.1010   0.8098   1.0000
   2.000   0.6026   0.03100   0.02039  -0.1022   0.7949   1.0000
   2.250   0.6363   0.03135   0.02067  -0.1028   0.7803   1.0000
   2.500   0.6689   0.03170   0.02097  -0.1032   0.7658   1.0000
   2.750   0.7001   0.03208   0.02131  -0.1033   0.7514   1.0000
   3.000   0.7302   0.03247   0.02171  -0.1033   0.7372   1.0000
   3.250   0.7593   0.03290   0.02214  -0.1030   0.7233   1.0000
   3.500   0.7877   0.03334   0.02259  -0.1026   0.7096   1.0000
   3.750   0.8161   0.03377   0.02304  -0.1021   0.6962   1.0000
   4.000   0.8467   0.03405   0.02340  -0.1018   0.6837   1.0000
   4.250   0.8767   0.03434   0.02374  -0.1013   0.6712   1.0000
   4.500   0.8976   0.03523   0.02470  -0.1003   0.6576   1.0000
   4.750   0.9176   0.03622   0.02577  -0.0992   0.6441   1.0000
   5.000   0.9361   0.03736   0.02706  -0.0980   0.6309   1.0000
   5.250   0.9531   0.03868   0.02848  -0.0969   0.6181   1.0000
   5.500   0.9694   0.04010   0.03001  -0.0957   0.6058   1.0000
   5.750   0.9874   0.04145   0.03149  -0.0947   0.5943   1.0000
   6.000   1.0278   0.04102   0.03127  -0.0946   0.5856   1.0000
   6.250   1.0324   0.04353   0.03392  -0.0931   0.5732   1.0000
   6.500   1.0307   0.04669   0.03720  -0.0914   0.5613   1.0000
   6.750   1.0307   0.04981   0.04043  -0.0900   0.5503   1.0000
   7.000   1.0808   0.04865   0.03955  -0.0900   0.5430   1.0000
   7.250   1.0462   0.05497   0.04588  -0.0879   0.5313   1.0000
   7.500   0.9985   0.06258   0.05338  -0.0863   0.5215   1.0000
   7.750   1.0730   0.05933   0.05066  -0.0861   0.5142   1.0000
   8.000   0.9784   0.07167   0.06256  -0.0856   0.5067   1.0000
   8.250   1.0069   0.07285   0.06400  -0.0851   0.4989   1.0000
   8.500   0.9683   0.08014   0.07120  -0.0856   0.4947   1.0000
   8.750   0.9734   0.08360   0.07479  -0.0856   0.4885   1.0000
   9.000   0.9705   0.08779   0.07908  -0.0857   0.4829   1.0000
   9.250   0.9548   0.09314   0.08447  -0.0865   0.4802   1.0000
   9.500   1.0373   0.08487   0.07688  -0.0795   0.4332   1.0000
   9.750   1.2184   0.04245   0.03283  -0.0481   0.1262   1.0000
  10.000   1.2090   0.04588   0.03614  -0.0460   0.1148   1.0000
  10.250   1.2037   0.04914   0.03937  -0.0444   0.1064   1.0000
  10.500   1.1994   0.05244   0.04255  -0.0428   0.0994   1.0000
  10.750   1.2031   0.05516   0.04541  -0.0413   0.0920   1.0000
  11.000   1.2274   0.05674   0.04695  -0.0385   0.0853   1.0000
  11.250   1.2899   0.05818   0.04856  -0.0365   0.0782   1.0000
  11.500   1.3327   0.06230   0.05291  -0.0366   0.0734   1.0000
  11.750   1.3390   0.06594   0.05698  -0.0351   0.0725   1.0000
  12.000   1.3417   0.07004   0.06147  -0.0337   0.0725   1.0000
  12.250   1.3373   0.07431   0.06610  -0.0324   0.0727   1.0000
  12.500   1.3283   0.07878   0.07089  -0.0315   0.0731   1.0000
  12.750   1.3156   0.08355   0.07594  -0.0311   0.0736   1.0000
  13.000   1.3012   0.08868   0.08132  -0.0312   0.0741   1.0000
  13.250   1.2859   0.09422   0.08707  -0.0320   0.0746   1.0000
  13.500   1.2737   0.10022   0.09326  -0.0331   0.0751   1.0000
  13.750   1.2411   0.10613   0.09946  -0.0364   0.0758   1.0000
  14.000   1.1930   0.11503   0.10862  -0.0433   0.0769   1.0000
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