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WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il)
Reynolds number: 100,000
Max Cl/Cd: 57.63 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60126-il-100000.txt
Download as CSV file: xf-fx60126-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3346   0.10237   0.09745  -0.0383   1.0000   0.1304
  -9.250  -0.3857   0.10079   0.09613  -0.0445   1.0000   0.1366
  -9.000  -0.4446   0.07572   0.07117  -0.0568   1.0000   0.0717
  -8.750  -0.4211   0.07600   0.07147  -0.0516   1.0000   0.0685
  -8.500  -0.5413   0.06296   0.05833  -0.0619   1.0000   0.0595
  -8.250  -0.5465   0.05963   0.05503  -0.0608   1.0000   0.0586
  -8.000  -0.5579   0.05559   0.05086  -0.0616   1.0000   0.0581
  -7.750  -0.5624   0.05131   0.04640  -0.0627   1.0000   0.0567
  -7.500  -0.5618   0.04628   0.04099  -0.0649   1.0000   0.0553
  -7.250  -0.5524   0.04102   0.03515  -0.0674   1.0000   0.0539
  -7.000  -0.5343   0.03625   0.02961  -0.0697   1.0000   0.0525
  -6.750  -0.5126   0.03315   0.02602  -0.0706   1.0000   0.0526
  -6.500  -0.4898   0.03087   0.02344  -0.0710   1.0000   0.0535
  -6.250  -0.4661   0.02895   0.02126  -0.0711   1.0000   0.0552
  -6.000  -0.4418   0.02727   0.01930  -0.0710   1.0000   0.0578
  -5.750  -0.4182   0.02566   0.01758  -0.0709   1.0000   0.0618
  -5.500  -0.3945   0.02465   0.01647  -0.0709   1.0000   0.0701
  -5.250  -0.3703   0.02321   0.01514  -0.0709   1.0000   0.0816
  -5.000  -0.3402   0.02167   0.01385  -0.0725   0.9991   0.1136
  -4.750  -0.2935   0.02052   0.01299  -0.0775   0.9938   0.1811
  -4.500  -0.2501   0.01971   0.01265  -0.0817   0.9872   0.2718
  -4.250  -0.2075   0.01993   0.01307  -0.0848   0.9803   0.3435
  -4.000  -0.1672   0.02049   0.01360  -0.0872   0.9721   0.3886
  -3.750  -0.1303   0.02103   0.01412  -0.0888   0.9633   0.4212
  -3.500  -0.0879   0.02163   0.01470  -0.0912   0.9557   0.4512
  -3.250  -0.0532   0.02192   0.01486  -0.0925   0.9453   0.4754
  -3.000  -0.0137   0.02223   0.01519  -0.0942   0.9372   0.4951
  -2.750   0.0222   0.02247   0.01542  -0.0953   0.9275   0.5143
  -2.500   0.0563   0.02265   0.01557  -0.0962   0.9180   0.5324
  -2.250   0.0980   0.02271   0.01558  -0.0984   0.9107   0.5510
  -2.000   0.1293   0.02276   0.01560  -0.0989   0.9004   0.5654
  -1.750   0.1748   0.02264   0.01543  -0.1017   0.8945   0.5815
  -1.500   0.2058   0.02259   0.01536  -0.1021   0.8834   0.5947
  -1.250   0.2562   0.02223   0.01494  -0.1056   0.8784   0.6092
  -1.000   0.2864   0.02211   0.01480  -0.1058   0.8667   0.6222
  -0.750   0.3272   0.02179   0.01445  -0.1076   0.8597   0.6367
  -0.500   0.3611   0.02157   0.01420  -0.1084   0.8497   0.6497
  -0.250   0.3916   0.02139   0.01404  -0.1084   0.8396   0.6601
   0.000   0.4294   0.02100   0.01365  -0.1095   0.8324   0.6723
   0.250   0.4581   0.02084   0.01349  -0.1093   0.8206   0.6845
   0.500   0.4932   0.02044   0.01308  -0.1098   0.8119   0.6981
   0.750   0.5245   0.02011   0.01276  -0.1097   0.8012   0.7117
   1.000   0.5506   0.01993   0.01263  -0.1088   0.7890   0.7239
   1.250   0.5803   0.01966   0.01238  -0.1084   0.7787   0.7370
   1.500   0.6113   0.01932   0.01206  -0.1082   0.7691   0.7508
   1.750   0.6371   0.01922   0.01199  -0.1075   0.7565   0.7649
   2.000   0.6639   0.01901   0.01183  -0.1067   0.7444   0.7807
   2.250   0.6923   0.01869   0.01152  -0.1059   0.7331   0.7982
   2.500   0.7205   0.01835   0.01119  -0.1051   0.7217   0.8181
   2.750   0.7432   0.01821   0.01114  -0.1036   0.7082   0.8403
   3.000   0.7648   0.01803   0.01105  -0.1018   0.6953   0.8685
   3.250   0.7854   0.01769   0.01082  -0.0997   0.6824   0.9126
   3.500   0.8245   0.01747   0.01060  -0.1018   0.6668   1.0000
   3.750   0.8610   0.01750   0.01051  -0.1036   0.6503   1.0000
   4.000   0.8941   0.01757   0.01047  -0.1045   0.6336   1.0000
   4.250   0.9249   0.01771   0.01053  -0.1049   0.6175   1.0000
   4.500   0.9542   0.01788   0.01062  -0.1050   0.6010   1.0000
   4.750   0.9825   0.01806   0.01072  -0.1048   0.5840   1.0000
   5.000   1.0101   0.01829   0.01088  -0.1045   0.5672   1.0000
   5.250   1.0372   0.01856   0.01109  -0.1042   0.5506   1.0000
   5.500   1.0636   0.01885   0.01131  -0.1037   0.5331   1.0000
   5.750   1.0876   0.01917   0.01167  -0.1029   0.5136   1.0000
   6.000   1.1118   0.01947   0.01195  -0.1020   0.4938   1.0000
   6.250   1.1361   0.01977   0.01220  -0.1012   0.4742   1.0000
   6.500   1.1595   0.02012   0.01251  -0.1003   0.4536   1.0000
   6.750   1.1810   0.02050   0.01292  -0.0991   0.4309   1.0000
   7.000   1.2032   0.02091   0.01324  -0.0980   0.4093   1.0000
   7.250   1.2228   0.02143   0.01378  -0.0966   0.3844   1.0000
   7.500   1.2418   0.02199   0.01427  -0.0951   0.3589   1.0000
   7.750   1.2592   0.02268   0.01484  -0.0934   0.3323   1.0000
   8.000   1.2752   0.02349   0.01559  -0.0917   0.3049   1.0000
   8.250   1.2909   0.02447   0.01645  -0.0899   0.2796   1.0000
   8.500   1.3061   0.02555   0.01737  -0.0882   0.2565   1.0000
   8.750   1.3205   0.02667   0.01845  -0.0863   0.2350   1.0000
   9.000   1.3343   0.02787   0.01955  -0.0846   0.2157   1.0000
   9.250   1.3477   0.02910   0.02069  -0.0827   0.1988   1.0000
   9.500   1.3613   0.03039   0.02190  -0.0810   0.1840   1.0000
   9.750   1.3756   0.03181   0.02330  -0.0794   0.1705   1.0000
  10.000   1.3900   0.03330   0.02483  -0.0779   0.1587   1.0000
  10.250   1.4062   0.03484   0.02632  -0.0766   0.1489   1.0000
  10.500   1.4235   0.03630   0.02774  -0.0755   0.1403   1.0000
  10.750   1.4378   0.03802   0.02961  -0.0740   0.1326   1.0000
  11.000   1.4662   0.04007   0.03144  -0.0747   0.1243   1.0000
  11.250   1.4711   0.04167   0.03344  -0.0719   0.1194   1.0000
  11.500   1.4885   0.04347   0.03530  -0.0709   0.1141   1.0000
  11.750   1.5131   0.04601   0.03789  -0.0711   0.1093   1.0000
  12.000   1.5175   0.04806   0.04027  -0.0686   0.1060   1.0000
  12.250   1.5249   0.05005   0.04245  -0.0667   0.1027   1.0000
  12.500   1.5577   0.05287   0.04513  -0.0681   0.0982   1.0000
  12.750   1.5482   0.05524   0.04793  -0.0644   0.0969   1.0000
  13.000   1.5392   0.05811   0.05117  -0.0614   0.0956   1.0000
  13.250   1.5288   0.06134   0.05474  -0.0589   0.0944   1.0000
  13.500   1.5162   0.06492   0.05864  -0.0568   0.0934   1.0000
  13.750   1.5007   0.06892   0.06295  -0.0552   0.0926   1.0000
  14.000   1.4814   0.07343   0.06776  -0.0542   0.0920   1.0000
  14.250   1.4568   0.07874   0.07337  -0.0540   0.0916   1.0000
  14.500   1.4231   0.08543   0.08037  -0.0550   0.0918   1.0000
  14.750   1.3773   0.09443   0.08970  -0.0582   0.0927   1.0000
  15.000   1.3162   0.10714   0.10269  -0.0650   0.0943   1.0000
  15.250   1.2390   0.12592   0.12167  -0.0771   0.0966   1.0000
  15.500   1.1796   0.14588   0.14168  -0.0895   0.0985   1.0000
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