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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 200,000
Max Cl/Cd: 69 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27-il-200000-n5.txt
Download as CSV file: xf-usa27-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2641   0.09195   0.08855  -0.0532   0.9850   0.0346
  -8.250  -0.2606   0.08673   0.08334  -0.0618   0.9761   0.0350
  -8.000  -0.2520   0.08118   0.07778  -0.0679   0.9682   0.0353
  -7.750  -0.2362   0.07906   0.07567  -0.0659   0.9660   0.0362
  -7.250  -0.2055   0.07255   0.06912  -0.0719   0.9550   0.0387
  -7.000  -0.1860   0.06791   0.06443  -0.0782   0.9501   0.0405
  -6.750  -0.1715   0.05888   0.05510  -0.0898   0.9383   0.0433
  -6.500  -0.1533   0.05667   0.05292  -0.0898   0.9358   0.0441
  -6.250  -0.1358   0.05506   0.05131  -0.0898   0.9308   0.0455
  -6.000  -0.1169   0.05244   0.04861  -0.0911   0.9238   0.0481
  -5.500  -0.0855   0.03509   0.02999  -0.0961   0.9072   0.0348
  -5.250  -0.0671   0.03155   0.02604  -0.0959   0.8991   0.0358
  -5.000  -0.0419   0.02897   0.02305  -0.0960   0.8904   0.0356
  -4.500   0.0107   0.02534   0.01878  -0.0957   0.8716   0.0349
  -4.250   0.0344   0.02372   0.01687  -0.0950   0.8615   0.0349
  -4.000   0.0606   0.02232   0.01519  -0.0947   0.8521   0.0349
  -3.750   0.0895   0.02086   0.01341  -0.0949   0.8432   0.0355
  -3.500   0.1145   0.01956   0.01195  -0.0945   0.8319   0.0362
  -3.250   0.1424   0.01860   0.01079  -0.0943   0.8206   0.0364
  -3.000   0.1713   0.01774   0.00973  -0.0943   0.8086   0.0364
  -2.750   0.1999   0.01697   0.00879  -0.0942   0.7952   0.0364
  -2.500   0.2273   0.01631   0.00799  -0.0939   0.7795   0.0366
  -2.250   0.2540   0.01572   0.00729  -0.0935   0.7617   0.0368
  -2.000   0.2806   0.01520   0.00667  -0.0931   0.7421   0.0371
  -1.750   0.3071   0.01476   0.00612  -0.0926   0.7216   0.0375
  -1.500   0.3329   0.01440   0.00565  -0.0920   0.7003   0.0379
  -1.250   0.3579   0.01414   0.00526  -0.0913   0.6797   0.0388
  -1.000   0.3824   0.01395   0.00496  -0.0905   0.6614   0.0402
  -0.750   0.4067   0.01380   0.00470  -0.0896   0.6453   0.0411
  -0.500   0.4309   0.01368   0.00448  -0.0888   0.6311   0.0415
  -0.250   0.4553   0.01360   0.00430  -0.0880   0.6182   0.0419
   0.000   0.4798   0.01356   0.00415  -0.0872   0.6058   0.0425
   0.500   0.5285   0.01349   0.00390  -0.0857   0.5799   0.0444
   0.750   0.5526   0.01348   0.00382  -0.0849   0.5665   0.0462
   1.000   0.5767   0.01348   0.00378  -0.0840   0.5529   0.0487
   1.250   0.6004   0.01348   0.00375  -0.0832   0.5392   0.0563
   1.500   0.6206   0.01310   0.00384  -0.0818   0.5251   0.2215
   1.750   0.6428   0.01308   0.00392  -0.0807   0.5094   0.2848
   2.000   0.6651   0.01310   0.00399  -0.0797   0.4935   0.3387
   2.250   0.6827   0.01257   0.00403  -0.0779   0.4790   0.5782
   2.750   0.8129   0.01272   0.00466  -0.0939   0.4418   1.0000
   3.000   0.8330   0.01295   0.00479  -0.0924   0.4316   1.0000
   3.250   0.8532   0.01318   0.00493  -0.0909   0.4220   1.0000
   3.500   0.8739   0.01339   0.00508  -0.0896   0.4142   1.0000
   3.750   0.8946   0.01362   0.00525  -0.0882   0.4071   1.0000
   4.000   0.9153   0.01385   0.00542  -0.0868   0.4007   1.0000
   4.250   0.9362   0.01406   0.00561  -0.0855   0.3939   1.0000
   4.750   0.9775   0.01453   0.00602  -0.0829   0.3810   1.0000
   5.000   0.9978   0.01477   0.00623  -0.0815   0.3747   1.0000
   5.250   1.0183   0.01502   0.00646  -0.0801   0.3688   1.0000
   5.500   1.0387   0.01525   0.00670  -0.0788   0.3620   1.0000
   5.750   1.0583   0.01553   0.00695  -0.0773   0.3562   1.0000
   6.000   1.0795   0.01575   0.00721  -0.0761   0.3511   1.0000
   6.250   1.1001   0.01600   0.00750  -0.0748   0.3458   1.0000
   6.500   1.1200   0.01629   0.00779  -0.0735   0.3408   1.0000
   6.750   1.1406   0.01653   0.00809  -0.0722   0.3350   1.0000
   7.000   1.1582   0.01683   0.00837  -0.0704   0.3255   1.0000
   7.250   1.1758   0.01709   0.00867  -0.0687   0.3139   1.0000
   7.500   1.1927   0.01741   0.00899  -0.0668   0.3028   1.0000
   7.750   1.2081   0.01775   0.00932  -0.0647   0.2927   1.0000
   8.000   1.2241   0.01808   0.00967  -0.0627   0.2794   1.0000
   8.250   1.2388   0.01847   0.01007  -0.0606   0.2641   1.0000
   8.500   1.2516   0.01897   0.01051  -0.0582   0.2407   1.0000
   8.750   1.2608   0.01969   0.01108  -0.0554   0.2113   1.0000
   9.000   1.2676   0.02065   0.01185  -0.0524   0.1852   1.0000
   9.250   1.2761   0.02159   0.01270  -0.0498   0.1684   1.0000
   9.500   1.2860   0.02249   0.01358  -0.0475   0.1547   1.0000
   9.750   1.2932   0.02358   0.01459  -0.0449   0.1351   1.0000
  10.000   1.2932   0.02516   0.01591  -0.0417   0.0921   1.0000
  10.250   1.2721   0.02825   0.01855  -0.0365   0.0297   1.0000
  10.500   1.2736   0.02996   0.02028  -0.0340   0.0231   1.0000
  10.750   1.2798   0.03138   0.02180  -0.0321   0.0212   1.0000
  11.000   1.2850   0.03293   0.02347  -0.0302   0.0199   1.0000
  11.250   1.2889   0.03466   0.02535  -0.0285   0.0188   1.0000
  11.500   1.2938   0.03638   0.02720  -0.0270   0.0181   1.0000
  11.750   1.2979   0.03823   0.02920  -0.0257   0.0174   1.0000
  12.000   1.3004   0.04031   0.03143  -0.0244   0.0166   1.0000
  12.250   1.3011   0.04266   0.03392  -0.0234   0.0160   1.0000
  12.500   1.3000   0.04531   0.03672  -0.0226   0.0155   1.0000
  12.750   1.2972   0.04829   0.03986  -0.0220   0.0151   1.0000
  13.000   1.2924   0.05167   0.04342  -0.0217   0.0148   1.0000
  13.250   1.2853   0.05549   0.04740  -0.0217   0.0146   1.0000
  13.500   1.2761   0.05973   0.05180  -0.0220   0.0144   1.0000
  13.750   1.2651   0.06435   0.05659  -0.0226   0.0142   1.0000
  14.000   1.2528   0.06932   0.06171  -0.0234   0.0141   1.0000
  14.250   1.2409   0.07436   0.06688  -0.0245   0.0139   1.0000
  14.500   1.2324   0.07901   0.07167  -0.0255   0.0139   1.0000
  14.750   1.2242   0.08372   0.07651  -0.0266   0.0137   1.0000
  15.000   1.2162   0.08844   0.08135  -0.0278   0.0136   1.0000
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