Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 438 AIRFOIL (goe438-il)
Reynolds number: 500,000
Max Cl/Cd: 95.04 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe438-il-500000.txt
Download as CSV file: xf-goe438-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 438 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2739   0.10121   0.09895  -0.0360   1.0000   0.0364
 -10.500  -0.3731   0.10202   0.09960  -0.0355   1.0000   0.0354
 -10.250  -0.3663   0.09995   0.09754  -0.0352   1.0000   0.0358
 -10.000  -0.3598   0.09808   0.09569  -0.0349   1.0000   0.0367
  -9.750  -0.3586   0.09533   0.09296  -0.0353   1.0000   0.0380
  -9.500  -0.3163   0.07936   0.07722  -0.0398   1.0000   0.0411
  -9.250  -0.3101   0.07859   0.07648  -0.0373   1.0000   0.0416
  -9.000  -0.3115   0.07731   0.07523  -0.0349   1.0000   0.0421
  -8.750  -0.3010   0.07425   0.07217  -0.0367   0.9986   0.0435
  -8.500  -0.4371   0.07206   0.06991  -0.0442   0.9966   0.0400
  -8.250  -0.3430   0.04809   0.04584  -0.0691   0.9842   0.0474
  -8.000  -0.3844   0.06988   0.06771  -0.0484   0.9912   0.0450
  -7.750  -0.3822   0.05018   0.04761  -0.0733   0.9791   0.0485
  -7.500  -0.3527   0.05113   0.04863  -0.0731   0.9763   0.0494
  -7.250  -0.2976   0.02510   0.02205  -0.0848   0.9632   0.0566
  -7.000  -0.2687   0.02394   0.02099  -0.0860   0.9599   0.0574
  -6.750  -0.2396   0.02268   0.01974  -0.0875   0.9566   0.0584
  -6.500  -0.2180   0.02132   0.01833  -0.0877   0.9485   0.0599
  -6.250  -0.1909   0.02010   0.01658  -0.0884   0.9407   0.0658
  -6.000  -0.1892   0.01413   0.01029  -0.0878   0.9290   0.0675
  -5.750  -0.1668   0.01291   0.00906  -0.0876   0.9196   0.0684
  -5.500  -0.1442   0.01179   0.00786  -0.0873   0.9098   0.0695
  -5.250  -0.1235   0.01081   0.00676  -0.0865   0.8980   0.0709
  -5.000  -0.1014   0.00993   0.00572  -0.0858   0.8869   0.0736
  -4.750  -0.0877   0.01732   0.01192  -0.0875   0.8971   0.0600
  -4.500  -0.0623   0.01637   0.01081  -0.0869   0.8859   0.0606
  -4.250  -0.0359   0.01548   0.00973  -0.0864   0.8751   0.0610
  -4.000  -0.0100   0.01462   0.00870  -0.0858   0.8637   0.0611
  -3.750   0.0157   0.01393   0.00787  -0.0852   0.8522   0.0615
  -3.500   0.0420   0.01332   0.00713  -0.0846   0.8409   0.0620
  -3.000   0.0942   0.01240   0.00600  -0.0834   0.8167   0.0634
  -2.750   0.1203   0.01210   0.00561  -0.0828   0.8040   0.0644
  -2.500   0.1463   0.01179   0.00523  -0.0822   0.7907   0.0650
  -2.250   0.1721   0.01151   0.00486  -0.0816   0.7768   0.0655
  -2.000   0.1979   0.01129   0.00457  -0.0809   0.7613   0.0659
  -1.750   0.2220   0.01062   0.00385  -0.0800   0.7445   0.0671
  -1.500   0.2463   0.01023   0.00341  -0.0791   0.7261   0.0684
  -1.250   0.2709   0.01002   0.00313  -0.0782   0.7067   0.0698
  -1.000   0.2956   0.00990   0.00294  -0.0774   0.6878   0.0714
  -0.750   0.3203   0.00982   0.00278  -0.0766   0.6704   0.0734
  -0.500   0.3453   0.00975   0.00263  -0.0758   0.6549   0.0750
  -0.250   0.3706   0.00970   0.00251  -0.0752   0.6407   0.0766
   0.000   0.3961   0.00967   0.00243  -0.0745   0.6273   0.0779
   0.250   0.4211   0.00954   0.00225  -0.0738   0.6152   0.0813
   0.500   0.4464   0.00951   0.00218  -0.0731   0.6032   0.0857
   0.750   0.4721   0.00949   0.00213  -0.0725   0.5905   0.0906
   1.000   0.4976   0.00943   0.00210  -0.0719   0.5778   0.1036
   1.250   0.5172   0.00862   0.00213  -0.0707   0.5658   0.4029
   1.500   0.5918   0.00739   0.00241  -0.0805   0.5470   0.9883
   1.750   0.6422   0.00754   0.00243  -0.0853   0.5273   1.0000
   2.000   0.6642   0.00767   0.00246  -0.0840   0.5102   1.0000
   2.250   0.6859   0.00782   0.00251  -0.0827   0.4923   1.0000
   2.500   0.7077   0.00799   0.00257  -0.0814   0.4749   1.0000
   2.750   0.7296   0.00817   0.00266  -0.0801   0.4581   1.0000
   3.000   0.7512   0.00837   0.00276  -0.0788   0.4395   1.0000
   3.250   0.7729   0.00858   0.00287  -0.0775   0.4225   1.0000
   3.500   0.7948   0.00880   0.00300  -0.0762   0.4080   1.0000
   3.750   0.8168   0.00902   0.00314  -0.0750   0.3957   1.0000
   4.000   0.8394   0.00921   0.00327  -0.0739   0.3835   1.0000
   4.250   0.8622   0.00940   0.00342  -0.0729   0.3721   1.0000
   4.500   0.8846   0.00962   0.00357  -0.0717   0.3614   1.0000
   4.750   0.9071   0.00982   0.00373  -0.0706   0.3515   1.0000
   5.000   0.9302   0.01001   0.00390  -0.0697   0.3423   1.0000
   5.250   0.9521   0.01025   0.00408  -0.0685   0.3332   1.0000
   5.500   0.9757   0.01041   0.00425  -0.0676   0.3251   1.0000
   5.750   0.9977   0.01066   0.00445  -0.0665   0.3173   1.0000
   6.000   1.0214   0.01082   0.00463  -0.0656   0.3098   1.0000
   6.500   1.0669   0.01125   0.00505  -0.0637   0.2950   1.0000
   7.000   1.1120   0.01170   0.00549  -0.0617   0.2783   1.0000
   7.250   1.1335   0.01197   0.00573  -0.0605   0.2707   1.0000
   7.500   1.1566   0.01217   0.00596  -0.0596   0.2626   1.0000
   7.750   1.1780   0.01245   0.00622  -0.0585   0.2542   1.0000
   8.000   1.1999   0.01269   0.00648  -0.0574   0.2449   1.0000
   8.250   1.2212   0.01297   0.00676  -0.0563   0.2353   1.0000
   8.500   1.2414   0.01329   0.00706  -0.0550   0.2236   1.0000
   8.750   1.2606   0.01367   0.00740  -0.0536   0.2070   1.0000
   9.000   1.2769   0.01420   0.00780  -0.0517   0.1836   1.0000
   9.250   1.2900   0.01489   0.00833  -0.0494   0.1531   1.0000
   9.500   1.2979   0.01576   0.00900  -0.0462   0.1230   1.0000
   9.750   1.3056   0.01661   0.00972  -0.0429   0.1007   1.0000
  10.000   1.3125   0.01752   0.01049  -0.0397   0.0774   1.0000
  10.250   1.3218   0.01833   0.01123  -0.0370   0.0679   1.0000
  10.500   1.3329   0.01906   0.01197  -0.0346   0.0642   1.0000
  10.750   1.3423   0.01988   0.01281  -0.0321   0.0608   1.0000
  11.000   1.3527   0.02067   0.01365  -0.0298   0.0583   1.0000
  11.250   1.3644   0.02141   0.01448  -0.0278   0.0566   1.0000
  11.500   1.3738   0.02230   0.01544  -0.0257   0.0547   1.0000
  11.750   1.3805   0.02340   0.01659  -0.0234   0.0527   1.0000
  12.000   1.3823   0.02486   0.01811  -0.0208   0.0504   1.0000
  12.250   1.3912   0.02594   0.01927  -0.0192   0.0488   1.0000
  12.500   1.4022   0.02692   0.02034  -0.0178   0.0469   1.0000
  12.750   1.4103   0.02815   0.02164  -0.0164   0.0450   1.0000
  13.000   1.4129   0.02987   0.02340  -0.0148   0.0427   1.0000
  13.250   1.4160   0.03164   0.02526  -0.0134   0.0407   1.0000
  13.500   1.4292   0.03264   0.02634  -0.0127   0.0379   1.0000
  13.750   1.4338   0.03443   0.02815  -0.0117   0.0353   1.0000
  14.000   1.4403   0.03613   0.02993  -0.0110   0.0323   1.0000
  14.250   1.4445   0.03811   0.03194  -0.0104   0.0295   1.0000
  14.500   1.4450   0.04059   0.03448  -0.0099   0.0272   1.0000
  14.750   1.4465   0.04305   0.03700  -0.0097   0.0254   1.0000
  15.000   1.4411   0.04640   0.04040  -0.0097   0.0239   1.0000
  15.250   1.4378   0.04963   0.04374  -0.0098   0.0231   1.0000
  15.500   1.4335   0.05310   0.04731  -0.0102   0.0223   1.0000
  15.750   1.4279   0.05681   0.05113  -0.0108   0.0216   1.0000
  16.000   1.4192   0.06106   0.05545  -0.0116   0.0207   1.0000
  16.250   1.4089   0.06568   0.06017  -0.0128   0.0202   1.0000
  16.500   1.3948   0.07091   0.06550  -0.0142   0.0198   1.0000
  16.750   1.3846   0.07575   0.07046  -0.0156   0.0194   1.0000
  17.000   1.3767   0.08034   0.07517  -0.0170   0.0191   1.0000
  17.250   1.3671   0.08525   0.08019  -0.0186   0.0187   1.0000
  17.500   1.3582   0.09013   0.08517  -0.0203   0.0183   1.0000
<< Back to GOE 438 AIRFOIL (goe438-il)

Polar data table (+)

Polar graphs


<< Back to GOE 438 AIRFOIL (goe438-il)