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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 500,000
Max Cl/Cd: 95.42 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa27-il-500000.txt
Download as CSV file: xf-usa27-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3138   0.11868   0.11644  -0.0305   1.0000   0.0214
 -10.250  -0.3209   0.11607   0.11386  -0.0303   1.0000   0.0221
 -10.000  -0.3311   0.11307   0.11090  -0.0317   0.9997   0.0224
  -9.750  -0.3225   0.10792   0.10574  -0.0375   0.9978   0.0225
  -9.500  -0.3129   0.10283   0.10065  -0.0429   0.9959   0.0225
  -9.250  -0.3007   0.09891   0.09674  -0.0432   0.9950   0.0228
  -9.000  -0.2838   0.09595   0.09378  -0.0450   0.9939   0.0231
  -8.750  -0.2691   0.09281   0.09064  -0.0474   0.9913   0.0236
  -8.500  -0.2547   0.08928   0.08710  -0.0511   0.9886   0.0242
  -8.250  -0.2398   0.08528   0.08310  -0.0559   0.9860   0.0249
  -8.000  -0.2237   0.08061   0.07842  -0.0626   0.9837   0.0260
  -7.750  -0.2087   0.07172   0.06948  -0.0797   0.9732   0.0273
  -7.250  -0.1789   0.06088   0.05854  -0.0897   0.9632   0.0279
  -7.000  -0.1522   0.05815   0.05579  -0.0931   0.9610   0.0284
  -6.750  -0.1230   0.05472   0.05231  -0.0979   0.9588   0.0291
  -6.500  -0.1059   0.05135   0.04886  -0.1000   0.9506   0.0300
  -6.250  -0.0757   0.04122   0.03815  -0.1087   0.9445   0.0333
  -6.000  -0.0718   0.03539   0.03211  -0.1081   0.9348   0.0340
  -5.750  -0.0463   0.03346   0.03018  -0.1092   0.9302   0.0346
  -5.500  -0.0277   0.03208   0.02875  -0.1085   0.9222   0.0353
  -5.250  -0.0045   0.03011   0.02664  -0.1088   0.9162   0.0367
  -5.000   0.0182   0.02887   0.02486  -0.1075   0.9077   0.0405
  -4.750   0.0330   0.02437   0.02006  -0.1068   0.9005   0.0422
  -4.500   0.0542   0.02307   0.01873  -0.1060   0.8913   0.0432
  -4.250   0.0801   0.02185   0.01738  -0.1060   0.8838   0.0450
  -4.000   0.1054   0.02210   0.01736  -0.1048   0.8734   0.0492
  -3.750   0.1237   0.01926   0.01428  -0.1038   0.8639   0.0523
  -3.500   0.1494   0.01842   0.01339  -0.1036   0.8539   0.0551
  -3.250   0.1716   0.01765   0.01232  -0.1023   0.8414   0.0629
  -3.000   0.1958   0.01669   0.01136  -0.1018   0.8285   0.0661
  -2.750   0.2245   0.01838   0.01288  -0.1011   0.8137   0.0733
  -2.000   0.2985   0.01240   0.00596  -0.0972   0.7639   0.0451
  -1.750   0.3233   0.01180   0.00516  -0.0960   0.7411   0.0428
  -1.250   0.3708   0.01155   0.00457  -0.0937   0.6891   0.0410
  -0.750   0.4169   0.01100   0.00380  -0.0914   0.6517   0.0406
  -0.250   0.4641   0.01062   0.00327  -0.0894   0.6243   0.0409
   0.000   0.4877   0.01042   0.00302  -0.0884   0.6121   0.0413
   0.250   0.5114   0.01030   0.00284  -0.0875   0.5995   0.0419
   0.500   0.5350   0.01022   0.00270  -0.0866   0.5852   0.0437
   0.750   0.5587   0.01020   0.00261  -0.0856   0.5696   0.0451
   1.000   0.5827   0.01021   0.00255  -0.0847   0.5532   0.0463
   1.250   0.6066   0.01023   0.00249  -0.0839   0.5364   0.0483
   1.500   0.6304   0.01027   0.00247  -0.0830   0.5185   0.0538
   1.750   0.6510   0.00999   0.00255  -0.0816   0.5003   0.2133
   2.000   0.6728   0.00995   0.00267  -0.0805   0.4823   0.3079
   2.250   0.6908   0.00954   0.00274  -0.0788   0.4662   0.5253
   2.500   0.7977   0.00926   0.00337  -0.0961   0.4402   0.9957
   2.750   0.8422   0.00949   0.00347  -0.1000   0.4265   1.0000
   3.000   0.8627   0.00970   0.00358  -0.0986   0.4168   1.0000
   3.250   0.8846   0.00984   0.00369  -0.0974   0.4086   1.0000
   3.750   0.9268   0.01018   0.00394  -0.0948   0.3947   1.0000
   4.000   0.9473   0.01037   0.00408  -0.0933   0.3880   1.0000
   4.250   0.9685   0.01053   0.00422  -0.0920   0.3824   1.0000
   4.500   0.9896   0.01068   0.00436  -0.0907   0.3765   1.0000
   4.750   1.0095   0.01090   0.00452  -0.0892   0.3708   1.0000
   5.000   1.0308   0.01103   0.00467  -0.0879   0.3657   1.0000
   5.250   1.0516   0.01119   0.00483  -0.0865   0.3604   1.0000
   5.500   1.0705   0.01143   0.00501  -0.0849   0.3542   1.0000
   5.750   1.0917   0.01154   0.00515  -0.0836   0.3469   1.0000
   6.000   1.1102   0.01176   0.00533  -0.0818   0.3394   1.0000
   6.250   1.1310   0.01189   0.00548  -0.0805   0.3322   1.0000
   6.500   1.1495   0.01211   0.00567  -0.0787   0.3247   1.0000
   6.750   1.1699   0.01226   0.00585  -0.0774   0.3175   1.0000
   7.000   1.1874   0.01251   0.00606  -0.0755   0.3083   1.0000
   7.250   1.2073   0.01267   0.00624  -0.0740   0.2979   1.0000
   7.500   1.2252   0.01291   0.00645  -0.0722   0.2852   1.0000
   7.750   1.2416   0.01318   0.00669  -0.0701   0.2698   1.0000
   8.000   1.2564   0.01355   0.00696  -0.0678   0.2494   1.0000
   8.250   1.2676   0.01417   0.00738  -0.0650   0.2125   1.0000
   8.500   1.2745   0.01509   0.00804  -0.0617   0.1772   1.0000
   8.750   1.2850   0.01589   0.00869  -0.0590   0.1550   1.0000
   9.000   1.2962   0.01666   0.00935  -0.0564   0.1325   1.0000
   9.250   1.2920   0.01836   0.01060  -0.0518   0.0723   1.0000
   9.500   1.2852   0.02026   0.01224  -0.0469   0.0247   1.0000
   9.750   1.2966   0.02110   0.01313  -0.0448   0.0219   1.0000
  10.000   1.3085   0.02193   0.01404  -0.0427   0.0202   1.0000
  10.250   1.3206   0.02276   0.01496  -0.0409   0.0193   1.0000
  10.500   1.3309   0.02373   0.01604  -0.0389   0.0183   1.0000
  10.750   1.3393   0.02486   0.01726  -0.0368   0.0176   1.0000
  11.000   1.3448   0.02624   0.01874  -0.0345   0.0170   1.0000
  11.250   1.3466   0.02795   0.02056  -0.0321   0.0164   1.0000
  11.500   1.3465   0.02988   0.02261  -0.0298   0.0161   1.0000
  11.750   1.3516   0.03151   0.02433  -0.0281   0.0158   1.0000
  12.000   1.3546   0.03337   0.02631  -0.0265   0.0156   1.0000
  12.250   1.3559   0.03550   0.02854  -0.0251   0.0153   1.0000
  12.500   1.3558   0.03787   0.03101  -0.0239   0.0150   1.0000
  12.750   1.3542   0.04052   0.03376  -0.0229   0.0147   1.0000
  13.000   1.3515   0.04345   0.03681  -0.0222   0.0144   1.0000
  13.250   1.3479   0.04667   0.04013  -0.0218   0.0141   1.0000
  13.500   1.3428   0.05019   0.04376  -0.0217   0.0139   1.0000
  13.750   1.3365   0.05398   0.04765  -0.0218   0.0136   1.0000
  14.000   1.3290   0.05800   0.05178  -0.0220   0.0135   1.0000
  14.250   1.3206   0.06219   0.05607  -0.0224   0.0133   1.0000
  14.500   1.3118   0.06650   0.06046  -0.0228   0.0132   1.0000
  14.750   1.3029   0.07087   0.06491  -0.0233   0.0131   1.0000
  15.000   1.2944   0.07514   0.06926  -0.0238   0.0130   1.0000
  15.250   1.2872   0.07912   0.07329  -0.0240   0.0128   1.0000
  15.500   1.2829   0.08235   0.07654  -0.0236   0.0127   1.0000
  15.750   1.2839   0.08500   0.07922  -0.0232   0.0125   1.0000
  16.000   1.2846   0.08820   0.08252  -0.0237   0.0124   1.0000
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