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J5012 12% (j5012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: J5012 12% (j5012-il)
Reynolds number: 100,000
Max Cl/Cd: 38.12 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-j5012-il-100000-n5.txt
Download as CSV file: xf-j5012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: J5012   12%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8109   0.08511   0.07909  -0.0403   1.0000   0.0329
 -13.750  -0.8377   0.07727   0.07109  -0.0452   1.0000   0.0328
 -13.500  -0.8635   0.07056   0.06417  -0.0489   1.0000   0.0327
 -13.250  -0.8847   0.06514   0.05855  -0.0510   1.0000   0.0327
 -13.000  -0.9074   0.06034   0.05348  -0.0522   1.0000   0.0328
 -12.750  -0.9245   0.05642   0.04931  -0.0520   1.0000   0.0329
 -12.500  -0.9318   0.05351   0.04630  -0.0511   1.0000   0.0334
 -12.250  -0.9341   0.05142   0.04415  -0.0500   1.0000   0.0341
 -12.000  -0.9398   0.04901   0.04158  -0.0482   1.0000   0.0345
 -11.750  -0.9438   0.04688   0.03929  -0.0460   1.0000   0.0350
 -11.500  -0.9465   0.04492   0.03717  -0.0435   1.0000   0.0357
 -11.250  -0.9482   0.04294   0.03499  -0.0406   1.0000   0.0364
 -11.000  -0.9480   0.04106   0.03290  -0.0376   1.0000   0.0372
 -10.750  -0.9448   0.03923   0.03085  -0.0347   1.0000   0.0379
 -10.500  -0.9385   0.03743   0.02880  -0.0321   1.0000   0.0390
 -10.250  -0.9298   0.03581   0.02687  -0.0297   1.0000   0.0403
 -10.000  -0.9197   0.03436   0.02540  -0.0276   1.0000   0.0419
  -9.750  -0.9092   0.03322   0.02425  -0.0254   1.0000   0.0436
  -9.500  -0.8973   0.03202   0.02294  -0.0232   1.0000   0.0455
  -9.250  -0.8839   0.03075   0.02151  -0.0211   1.0000   0.0475
  -9.000  -0.8697   0.02955   0.02012  -0.0190   1.0000   0.0495
  -8.750  -0.8586   0.02837   0.01897  -0.0167   1.0000   0.0517
  -8.500  -0.8464   0.02747   0.01803  -0.0144   1.0000   0.0548
  -8.250  -0.8328   0.02659   0.01702  -0.0121   1.0000   0.0588
  -8.000  -0.8216   0.02561   0.01606  -0.0095   1.0000   0.0624
  -7.750  -0.8090   0.02480   0.01522  -0.0071   1.0000   0.0669
  -7.500  -0.7964   0.02400   0.01434  -0.0045   1.0000   0.0724
  -7.250  -0.7842   0.02323   0.01359  -0.0020   1.0000   0.0786
  -7.000  -0.7715   0.02250   0.01284   0.0005   1.0000   0.0861
  -6.750  -0.7583   0.02183   0.01215   0.0030   1.0000   0.0951
  -6.500  -0.7457   0.02113   0.01150   0.0055   1.0000   0.1055
  -6.250  -0.7325   0.02048   0.01088   0.0080   1.0000   0.1183
  -6.000  -0.7190   0.01986   0.01031   0.0104   1.0000   0.1340
  -5.750  -0.7052   0.01926   0.00979   0.0127   1.0000   0.1539
  -5.500  -0.6915   0.01867   0.00931   0.0150   1.0000   0.1782
  -5.250  -0.6776   0.01811   0.00889   0.0173   1.0000   0.2081
  -5.000  -0.6632   0.01760   0.00851   0.0196   1.0000   0.2418
  -4.750  -0.6491   0.01710   0.00819   0.0218   1.0000   0.2803
  -4.500  -0.6346   0.01666   0.00792   0.0240   1.0000   0.3215
  -4.250  -0.6200   0.01626   0.00770   0.0263   1.0000   0.3660
  -4.000  -0.5953   0.01587   0.00753   0.0265   0.9966   0.4192
  -3.750  -0.5639   0.01555   0.00742   0.0255   0.9906   0.4750
  -3.500  -0.5317   0.01531   0.00738   0.0244   0.9845   0.5281
  -3.250  -0.5003   0.01511   0.00733   0.0237   0.9781   0.5758
  -3.000  -0.4668   0.01499   0.00733   0.0227   0.9720   0.6200
  -2.750  -0.4345   0.01490   0.00733   0.0219   0.9654   0.6600
  -2.500  -0.3999   0.01486   0.00737   0.0208   0.9589   0.6961
  -2.250  -0.3633   0.01487   0.00742   0.0194   0.9533   0.7284
  -2.000  -0.3294   0.01488   0.00746   0.0185   0.9457   0.7563
  -1.750  -0.2878   0.01494   0.00752   0.0161   0.9409   0.7817
  -1.500  -0.2535   0.01499   0.00759   0.0152   0.9327   0.8037
  -1.250  -0.2104   0.01507   0.00765   0.0125   0.9273   0.8229
  -1.000  -0.1706   0.01514   0.00771   0.0105   0.9202   0.8398
  -0.750  -0.1278   0.01520   0.00776   0.0078   0.9135   0.8545
  -0.500  -0.0837   0.01524   0.00778   0.0049   0.9069   0.8672
  -0.250  -0.0445   0.01526   0.00779   0.0030   0.8976   0.8797
   0.000   0.0000   0.01529   0.00782   0.0000   0.8889   0.8889
   0.250   0.0445   0.01526   0.00779  -0.0030   0.8797   0.8976
   0.500   0.0836   0.01524   0.00778  -0.0049   0.8672   0.9069
   0.750   0.1277   0.01520   0.00776  -0.0078   0.8544   0.9134
   1.000   0.1706   0.01514   0.00771  -0.0105   0.8399   0.9203
   1.250   0.2104   0.01507   0.00765  -0.0125   0.8229   0.9273
   1.500   0.2535   0.01499   0.00759  -0.0152   0.8037   0.9327
   1.750   0.2879   0.01494   0.00752  -0.0161   0.7820   0.9409
   2.000   0.3294   0.01488   0.00746  -0.0185   0.7563   0.9457
   2.250   0.3633   0.01487   0.00742  -0.0194   0.7281   0.9533
   2.500   0.3999   0.01486   0.00736  -0.0208   0.6960   0.9590
   2.750   0.4345   0.01490   0.00733  -0.0219   0.6604   0.9654
   3.000   0.4669   0.01499   0.00733  -0.0227   0.6203   0.9720
   3.250   0.5004   0.01511   0.00733  -0.0237   0.5763   0.9781
   3.500   0.5317   0.01531   0.00738  -0.0244   0.5282   0.9845
   3.750   0.5639   0.01555   0.00742  -0.0255   0.4755   0.9906
   4.000   0.5953   0.01587   0.00753  -0.0265   0.4188   0.9966
   4.250   0.6199   0.01626   0.00770  -0.0263   0.3657   1.0000
   4.500   0.6345   0.01666   0.00792  -0.0240   0.3217   1.0000
   4.750   0.6491   0.01710   0.00819  -0.0218   0.2802   1.0000
   5.000   0.6632   0.01760   0.00851  -0.0196   0.2420   1.0000
   5.250   0.6776   0.01811   0.00888  -0.0173   0.2082   1.0000
   5.500   0.6915   0.01867   0.00931  -0.0150   0.1784   1.0000
   5.750   0.7052   0.01926   0.00979  -0.0127   0.1542   1.0000
   6.000   0.7190   0.01985   0.01031  -0.0104   0.1341   1.0000
   6.250   0.7326   0.02047   0.01088  -0.0080   0.1182   1.0000
   6.500   0.7458   0.02113   0.01150  -0.0055   0.1052   1.0000
   6.750   0.7583   0.02183   0.01215  -0.0030   0.0951   1.0000
   7.000   0.7715   0.02250   0.01284  -0.0005   0.0860   1.0000
   7.250   0.7842   0.02323   0.01358   0.0020   0.0785   1.0000
   7.500   0.7963   0.02400   0.01434   0.0045   0.0723   1.0000
   7.750   0.8090   0.02480   0.01522   0.0070   0.0669   1.0000
   8.000   0.8215   0.02560   0.01605   0.0095   0.0622   1.0000
   8.250   0.8328   0.02659   0.01702   0.0121   0.0587   1.0000
   8.500   0.8464   0.02749   0.01805   0.0144   0.0549   1.0000
   8.750   0.8586   0.02837   0.01896   0.0167   0.0516   1.0000
   9.000   0.8697   0.02956   0.02011   0.0190   0.0494   1.0000
   9.250   0.8839   0.03076   0.02152   0.0211   0.0474   1.0000
   9.500   0.8970   0.03201   0.02292   0.0233   0.0452   1.0000
   9.750   0.9087   0.03318   0.02418   0.0255   0.0433   1.0000
  10.000   0.9194   0.03432   0.02536   0.0276   0.0417   1.0000
  10.250   0.9298   0.03581   0.02688   0.0297   0.0403   1.0000
  10.500   0.9386   0.03742   0.02879   0.0321   0.0390   1.0000
  10.750   0.9447   0.03923   0.03085   0.0347   0.0379   1.0000
  11.000   0.9477   0.04107   0.03291   0.0376   0.0370   1.0000
  11.250   0.9483   0.04295   0.03499   0.0406   0.0364   1.0000
  11.500   0.9467   0.04496   0.03720   0.0434   0.0357   1.0000
  11.750   0.9438   0.04700   0.03943   0.0460   0.0352   1.0000
  12.000   0.9396   0.04913   0.04172   0.0482   0.0346   1.0000
  12.250   0.9347   0.05140   0.04413   0.0499   0.0340   1.0000
  12.500   0.9311   0.05367   0.04648   0.0511   0.0335   1.0000
  12.750   0.9253   0.05648   0.04939   0.0519   0.0330   1.0000
  13.000   0.9094   0.06030   0.05342   0.0521   0.0329   1.0000
  13.250   0.8885   0.06492   0.05830   0.0512   0.0328   1.0000
  13.500   0.8624   0.07080   0.06443   0.0486   0.0327   1.0000
  13.750   0.8384   0.07734   0.07116   0.0451   0.0328   1.0000
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