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NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NLR-7223-62 AIRFOIL (nl722362-il)
Reynolds number: 50,000
Max Cl/Cd: 28.51 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nl722362-il-50000-n5.txt
Download as CSV file: xf-nl722362-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-62 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4921   0.11030   0.10310  -0.0200   1.0000   0.1264
  -9.500  -0.4916   0.10704   0.09990  -0.0210   1.0000   0.1309
  -9.250  -0.5225   0.10495   0.09799  -0.0270   1.0000   0.1358
  -9.000  -0.4070   0.08614   0.07948  -0.0313   1.0000   0.0699
  -8.750  -0.4220   0.08029   0.07366  -0.0351   1.0000   0.0610
  -8.250  -0.5264   0.08221   0.07526  -0.0348   1.0000   0.0607
  -8.000  -0.5315   0.07872   0.07181  -0.0340   1.0000   0.0588
  -7.750  -0.5403   0.07513   0.06822  -0.0330   1.0000   0.0566
  -7.250  -0.5652   0.06781   0.06056  -0.0294   1.0000   0.0501
  -7.000  -0.5664   0.06475   0.05744  -0.0270   1.0000   0.0492
  -6.750  -0.5681   0.06179   0.05438  -0.0245   1.0000   0.0483
  -6.500  -0.5691   0.05879   0.05122  -0.0218   1.0000   0.0473
  -6.250  -0.5688   0.05570   0.04791  -0.0190   1.0000   0.0463
  -6.000  -0.5665   0.05261   0.04455  -0.0161   1.0000   0.0454
  -5.750  -0.5619   0.04960   0.04120  -0.0133   1.0000   0.0444
  -5.500  -0.5551   0.04661   0.03782  -0.0104   1.0000   0.0436
  -5.250  -0.5455   0.04377   0.03456  -0.0076   1.0000   0.0429
  -5.000  -0.5334   0.04119   0.03155  -0.0050   1.0000   0.0425
  -4.750  -0.5193   0.03881   0.02878  -0.0027   1.0000   0.0426
  -4.500  -0.5036   0.03683   0.02650  -0.0008   1.0000   0.0442
  -4.250  -0.4860   0.03494   0.02428   0.0011   1.0000   0.0459
  -4.000  -0.4663   0.03307   0.02202   0.0030   1.0000   0.0474
  -3.750  -0.4447   0.03129   0.01988   0.0045   1.0000   0.0483
  -3.500  -0.4215   0.02968   0.01795   0.0059   1.0000   0.0492
  -3.250  -0.3968   0.02824   0.01618   0.0071   1.0000   0.0507
  -3.000  -0.3727   0.02684   0.01478   0.0080   1.0000   0.0546
  -2.750  -0.3479   0.02586   0.01365   0.0089   1.0000   0.0594
  -2.500  -0.3221   0.02486   0.01245   0.0097   1.0000   0.0644
  -2.000  -0.1198   0.01952   0.01040  -0.0161   1.0000   1.0000
  -1.750  -0.1074   0.01947   0.01004  -0.0136   1.0000   1.0000
  -1.500  -0.0941   0.01945   0.00974  -0.0113   1.0000   1.0000
  -1.250  -0.0801   0.01945   0.00951  -0.0090   1.0000   1.0000
  -1.000  -0.0655   0.01948   0.00930  -0.0069   1.0000   1.0000
  -0.750  -0.0504   0.01953   0.00916  -0.0048   1.0000   1.0000
  -0.500  -0.0349   0.01961   0.00907  -0.0029   1.0000   1.0000
  -0.250  -0.0191   0.01971   0.00902  -0.0010   1.0000   1.0000
   0.000  -0.0030   0.01983   0.00901   0.0009   1.0000   1.0000
   0.250   0.0132   0.01997   0.00904   0.0026   1.0000   1.0000
   0.500   0.0297   0.02014   0.00911   0.0043   1.0000   1.0000
   0.750   0.0461   0.02033   0.00924   0.0060   1.0000   1.0000
   1.000   0.0627   0.02056   0.00940   0.0076   1.0000   1.0000
   1.250   0.1013   0.02097   0.00979   0.0046   0.9918   1.0000
   1.500   0.1674   0.02151   0.01035  -0.0036   0.9725   1.0000
   1.750   0.2503   0.02160   0.01053  -0.0142   0.9404   1.0000
   2.000   0.3229   0.02134   0.01040  -0.0222   0.9114   1.0000
   2.250   0.3786   0.02100   0.01023  -0.0268   0.8867   1.0000
   2.500   0.4154   0.02066   0.01002  -0.0276   0.8590   1.0000
   2.750   0.4446   0.02032   0.00981  -0.0269   0.8269   1.0000
   3.000   0.4580   0.02017   0.00981  -0.0234   0.7839   1.0000
   3.250   0.4681   0.02002   0.00976  -0.0192   0.7160   1.0000
   3.500   0.5439   0.01908   0.00800  -0.0241   0.5335   1.0000
   3.750   0.5603   0.01996   0.00828  -0.0214   0.4391   1.0000
   4.000   0.5766   0.02084   0.00878  -0.0192   0.3836   1.0000
   4.250   0.5955   0.02165   0.00935  -0.0176   0.3470   1.0000
   4.500   0.6159   0.02242   0.00996  -0.0164   0.3209   1.0000
   4.750   0.6384   0.02315   0.01061  -0.0154   0.3008   1.0000
   5.000   0.6625   0.02387   0.01135  -0.0147   0.2848   1.0000
   5.250   0.6875   0.02459   0.01208  -0.0142   0.2705   1.0000
   5.500   0.7133   0.02533   0.01285  -0.0138   0.2573   1.0000
   5.750   0.7385   0.02607   0.01372  -0.0134   0.2446   1.0000
   6.000   0.7632   0.02686   0.01465  -0.0128   0.2325   1.0000
   6.250   0.7868   0.02770   0.01562  -0.0121   0.2205   1.0000
   6.500   0.8096   0.02860   0.01661  -0.0112   0.2090   1.0000
   6.750   0.8315   0.02952   0.01762  -0.0103   0.1975   1.0000
   7.000   0.8511   0.03045   0.01878  -0.0090   0.1844   1.0000
   7.250   0.8696   0.03144   0.01998  -0.0075   0.1709   1.0000
   7.500   0.8867   0.03246   0.02122  -0.0059   0.1569   1.0000
   7.750   0.9010   0.03333   0.02224  -0.0039   0.1417   1.0000
   8.000   0.9136   0.03411   0.02316  -0.0016   0.1264   1.0000
   8.250   0.9253   0.03494   0.02411   0.0007   0.1119   1.0000
   8.500   0.9369   0.03603   0.02540   0.0030   0.0982   1.0000
   8.750   0.9484   0.03723   0.02676   0.0053   0.0872   1.0000
   9.000   0.9591   0.03856   0.02819   0.0076   0.0785   1.0000
   9.250   0.9694   0.04076   0.03069   0.0098   0.0714   1.0000
   9.500   0.9780   0.04213   0.03197   0.0121   0.0665   1.0000
   9.750   0.9833   0.04498   0.03535   0.0147   0.0619   1.0000
  10.000   0.9875   0.04744   0.03807   0.0172   0.0591   1.0000
  10.250   0.9916   0.04953   0.04027   0.0195   0.0569   1.0000
  10.500   0.9894   0.05238   0.04334   0.0222   0.0553   1.0000
  10.750   0.9762   0.05579   0.04716   0.0257   0.0541   1.0000
  11.000   0.9588   0.05927   0.05093   0.0289   0.0534   1.0000
  11.250   0.9382   0.06320   0.05511   0.0310   0.0530   1.0000
  11.500   0.9139   0.06796   0.06009   0.0317   0.0530   1.0000
  11.750   0.8864   0.07391   0.06622   0.0304   0.0535   1.0000
  12.000   0.8570   0.08142   0.07381   0.0266   0.0543   1.0000
  12.250   0.8296   0.09046   0.08290   0.0211   0.0552   1.0000
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