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WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il)
Reynolds number: 50,000
Max Cl/Cd: 39.13 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60126-il-50000-n5.txt
Download as CSV file: xf-fx60126-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3807   0.10240   0.09507  -0.0450   1.0000   0.0473
 -10.250  -0.3855   0.09757   0.09032  -0.0468   1.0000   0.0473
 -10.000  -0.3927   0.09240   0.08525  -0.0489   1.0000   0.0472
  -9.750  -0.4044   0.08641   0.07938  -0.0513   1.0000   0.0470
  -9.500  -0.4204   0.08003   0.07310  -0.0541   1.0000   0.0463
  -9.250  -0.4992   0.06605   0.05902  -0.0634   1.0000   0.0415
  -9.000  -0.5228   0.06222   0.05521  -0.0644   1.0000   0.0414
  -8.750  -0.5392   0.05852   0.05144  -0.0656   1.0000   0.0412
  -8.500  -0.5546   0.05466   0.04736  -0.0666   1.0000   0.0414
  -8.250  -0.5594   0.05140   0.04394  -0.0668   1.0000   0.0418
  -8.000  -0.5563   0.04899   0.04146  -0.0664   1.0000   0.0429
  -7.750  -0.5508   0.04640   0.03869  -0.0664   1.0000   0.0441
  -7.500  -0.5420   0.04371   0.03574  -0.0665   1.0000   0.0455
  -7.250  -0.5298   0.04093   0.03263  -0.0665   1.0000   0.0471
  -7.000  -0.5147   0.03840   0.02969  -0.0664   1.0000   0.0489
  -6.750  -0.4984   0.03647   0.02758  -0.0660   1.0000   0.0518
  -6.500  -0.4809   0.03494   0.02593  -0.0657   1.0000   0.0562
  -6.250  -0.4621   0.03325   0.02403  -0.0652   1.0000   0.0614
  -6.000  -0.4424   0.03182   0.02246  -0.0650   1.0000   0.0693
  -5.750  -0.4218   0.03042   0.02106  -0.0651   1.0000   0.0794
  -5.500  -0.3856   0.02880   0.01942  -0.0684   0.9945   0.1008
  -5.250  -0.3478   0.02730   0.01796  -0.0721   0.9883   0.1350
  -5.000  -0.3080   0.02592   0.01678  -0.0760   0.9827   0.1810
  -4.750  -0.2723   0.02500   0.01609  -0.0787   0.9756   0.2336
  -4.500  -0.2336   0.02481   0.01606  -0.0815   0.9691   0.2971
  -4.250  -0.2001   0.02495   0.01619  -0.0827   0.9604   0.3441
  -4.000  -0.1629   0.02519   0.01627  -0.0846   0.9528   0.3829
  -3.750  -0.1292   0.02546   0.01643  -0.0856   0.9438   0.4141
  -3.500  -0.0957   0.02575   0.01660  -0.0864   0.9353   0.4417
  -3.250  -0.0615   0.02596   0.01670  -0.0873   0.9270   0.4643
  -3.000  -0.0302   0.02607   0.01670  -0.0878   0.9181   0.4835
  -2.750   0.0062   0.02612   0.01660  -0.0893   0.9105   0.5029
  -2.500   0.0362   0.02615   0.01651  -0.0897   0.9009   0.5193
  -2.250   0.0750   0.02611   0.01634  -0.0916   0.8941   0.5357
  -2.000   0.1038   0.02609   0.01623  -0.0918   0.8834   0.5492
  -1.750   0.1419   0.02600   0.01603  -0.0934   0.8761   0.5645
  -1.500   0.1723   0.02594   0.01590  -0.0938   0.8657   0.5781
  -1.250   0.2042   0.02586   0.01572  -0.0945   0.8560   0.5910
  -1.000   0.2405   0.02572   0.01548  -0.0959   0.8480   0.6042
  -0.750   0.2690   0.02570   0.01540  -0.0961   0.8370   0.6168
  -0.500   0.3057   0.02551   0.01517  -0.0972   0.8300   0.6300
  -0.250   0.3321   0.02550   0.01515  -0.0969   0.8182   0.6420
   0.000   0.3612   0.02544   0.01506  -0.0969   0.8072   0.6548
   0.250   0.3977   0.02519   0.01477  -0.0980   0.7993   0.6681
   0.500   0.4244   0.02519   0.01476  -0.0977   0.7868   0.6811
   0.750   0.4517   0.02514   0.01473  -0.0974   0.7754   0.6938
   1.000   0.4860   0.02488   0.01448  -0.0979   0.7676   0.7078
   1.250   0.5104   0.02492   0.01457  -0.0971   0.7551   0.7221
   1.500   0.5364   0.02491   0.01461  -0.0966   0.7434   0.7379
   1.750   0.5654   0.02474   0.01449  -0.0962   0.7329   0.7551
   2.000   0.5945   0.02453   0.01433  -0.0958   0.7222   0.7740
   2.250   0.6177   0.02448   0.01439  -0.0946   0.7093   0.7939
   2.500   0.6416   0.02438   0.01439  -0.0935   0.6971   0.8180
   2.750   0.6670   0.02415   0.01428  -0.0923   0.6867   0.8502
   3.000   0.6956   0.02386   0.01414  -0.0919   0.6757   0.9177
   3.250   0.7284   0.02401   0.01429  -0.0931   0.6622   1.0000
   3.500   0.7604   0.02421   0.01443  -0.0940   0.6486   1.0000
   3.750   0.7916   0.02439   0.01457  -0.0945   0.6350   1.0000
   4.000   0.8223   0.02457   0.01474  -0.0949   0.6216   1.0000
   4.250   0.8531   0.02475   0.01489  -0.0952   0.6089   1.0000
   4.500   0.8836   0.02492   0.01502  -0.0953   0.5956   1.0000
   4.750   0.9118   0.02514   0.01526  -0.0951   0.5805   1.0000
   5.000   0.9382   0.02543   0.01555  -0.0946   0.5642   1.0000
   5.250   0.9637   0.02575   0.01587  -0.0940   0.5473   1.0000
   5.500   0.9887   0.02610   0.01626  -0.0934   0.5303   1.0000
   5.750   1.0125   0.02649   0.01669  -0.0926   0.5125   1.0000
   6.000   1.0359   0.02688   0.01710  -0.0916   0.4939   1.0000
   6.250   1.0592   0.02726   0.01751  -0.0907   0.4754   1.0000
   6.500   1.0822   0.02766   0.01792  -0.0897   0.4567   1.0000
   6.750   1.1022   0.02819   0.01849  -0.0884   0.4364   1.0000
   7.000   1.1214   0.02876   0.01911  -0.0871   0.4155   1.0000
   7.250   1.1413   0.02933   0.01969  -0.0858   0.3957   1.0000
   7.500   1.1604   0.03001   0.02039  -0.0845   0.3765   1.0000
   7.750   1.1767   0.03081   0.02124  -0.0829   0.3555   1.0000
   8.000   1.1920   0.03161   0.02204  -0.0812   0.3339   1.0000
   8.250   1.2047   0.03257   0.02300  -0.0793   0.3115   1.0000
   8.500   1.2160   0.03361   0.02400  -0.0773   0.2901   1.0000
   8.750   1.2267   0.03475   0.02507  -0.0753   0.2710   1.0000
   9.000   1.2352   0.03603   0.02637  -0.0732   0.2528   1.0000
   9.250   1.2437   0.03740   0.02776  -0.0712   0.2366   1.0000
   9.500   1.2522   0.03888   0.02922  -0.0693   0.2220   1.0000
   9.750   1.2597   0.04049   0.03083  -0.0676   0.2080   1.0000
  10.000   1.2668   0.04217   0.03250  -0.0659   0.1956   1.0000
  10.250   1.2748   0.04396   0.03438  -0.0644   0.1842   1.0000
  10.500   1.2834   0.04584   0.03634  -0.0631   0.1740   1.0000
  10.750   1.2920   0.04772   0.03821  -0.0618   0.1647   1.0000
  11.000   1.2976   0.04985   0.04048  -0.0606   0.1554   1.0000
  11.250   1.3032   0.05206   0.04279  -0.0595   0.1472   1.0000
  11.500   1.3103   0.05414   0.04490  -0.0585   0.1401   1.0000
  11.750   1.3156   0.05663   0.04757  -0.0577   0.1335   1.0000
  12.000   1.3220   0.05896   0.04997  -0.0569   0.1274   1.0000
  12.250   1.3298   0.06139   0.05250  -0.0562   0.1223   1.0000
  12.500   1.3295   0.06463   0.05604  -0.0557   0.1175   1.0000
  12.750   1.3346   0.06723   0.05874  -0.0553   0.1129   1.0000
  13.000   1.3369   0.07034   0.06200  -0.0550   0.1091   1.0000
  13.250   1.3296   0.07467   0.06666  -0.0553   0.1060   1.0000
  13.500   1.3250   0.07881   0.07104  -0.0557   0.1033   1.0000
  13.750   1.3256   0.08229   0.07465  -0.0559   0.1006   1.0000
  14.000   1.3315   0.08522   0.07761  -0.0559   0.0978   1.0000
  14.250   1.3075   0.09233   0.08509  -0.0585   0.0966   1.0000
  14.500   1.2781   0.10084   0.09393  -0.0623   0.0958   1.0000
  14.750   1.2381   0.11216   0.10553  -0.0685   0.0955   1.0000
  15.000   1.1697   0.13177   0.12535  -0.0810   0.0961   1.0000
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