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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 200,000
Max Cl/Cd: 71.09 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40-il-200000.txt
Download as CSV file: xf-usa40-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3548   0.09394   0.09048  -0.0432   1.0000   0.0789
  -8.500  -0.3934   0.09252   0.08919  -0.0402   1.0000   0.0790
  -8.250  -0.3553   0.08888   0.08553  -0.0370   1.0000   0.0800
  -8.000  -0.3583   0.08778   0.08449  -0.0333   1.0000   0.0806
  -7.750  -0.3698   0.08700   0.08378  -0.0294   1.0000   0.0811
  -7.500  -0.3466   0.08432   0.08110  -0.0318   0.9966   0.0830
  -7.250  -0.3315   0.06780   0.06444  -0.0671   0.9805   0.0913
  -7.000  -0.3019   0.06679   0.06350  -0.0650   0.9758   0.0923
  -6.750  -0.2675   0.06444   0.06114  -0.0674   0.9715   0.0941
  -6.500  -0.2515   0.03543   0.03043  -0.1017   0.9567   0.0673
  -6.250  -0.2188   0.03101   0.02557  -0.1054   0.9480   0.0653
  -6.000  -0.1766   0.02727   0.02131  -0.1100   0.9436   0.0646
  -5.750  -0.1327   0.02435   0.01790  -0.1139   0.9407   0.0641
  -5.500  -0.1014   0.02264   0.01592  -0.1148   0.9309   0.0644
  -5.250  -0.0613   0.02105   0.01409  -0.1171   0.9259   0.0654
  -5.000  -0.0296   0.01993   0.01277  -0.1176   0.9160   0.0667
  -4.750   0.0075   0.01904   0.01164  -0.1189   0.9090   0.0688
  -4.500   0.0360   0.01779   0.01037  -0.1189   0.8975   0.0708
  -4.250   0.0684   0.01691   0.00949  -0.1194   0.8884   0.0731
  -4.000   0.0970   0.01623   0.00876  -0.1191   0.8758   0.0759
  -3.750   0.1255   0.01570   0.00812  -0.1187   0.8628   0.0789
  -3.500   0.1536   0.01484   0.00735  -0.1185   0.8505   0.0842
  -3.250   0.1823   0.01434   0.00677  -0.1182   0.8377   0.0910
  -3.000   0.2091   0.01373   0.00621  -0.1178   0.8229   0.1010
  -2.750   0.2368   0.01318   0.00569  -0.1175   0.8085   0.1175
  -2.500   0.2648   0.01267   0.00534  -0.1174   0.7945   0.1493
  -2.250   0.2928   0.01227   0.00511  -0.1172   0.7803   0.2146
  -2.000   0.3204   0.01192   0.00491  -0.1171   0.7656   0.2732
  -1.750   0.3475   0.01164   0.00482  -0.1168   0.7499   0.3350
  -1.500   0.3745   0.01139   0.00476  -0.1165   0.7342   0.4100
  -1.250   0.4008   0.01113   0.00475  -0.1159   0.7183   0.4958
  -1.000   0.4263   0.01100   0.00483  -0.1150   0.7025   0.5829
  -0.750   0.4517   0.01103   0.00493  -0.1139   0.6866   0.6469
  -0.500   0.4769   0.01114   0.00502  -0.1127   0.6704   0.6959
  -0.250   0.5018   0.01127   0.00510  -0.1115   0.6539   0.7332
   0.000   0.5260   0.01140   0.00516  -0.1102   0.6374   0.7633
   0.250   0.5499   0.01152   0.00520  -0.1088   0.6210   0.7913
   0.500   0.5734   0.01160   0.00522  -0.1074   0.6044   0.8161
   0.750   0.5969   0.01165   0.00521  -0.1060   0.5873   0.8390
   1.000   0.6195   0.01166   0.00518  -0.1045   0.5706   0.8602
   1.250   0.6421   0.01165   0.00514  -0.1031   0.5545   0.8840
   1.500   0.6655   0.01163   0.00508  -0.1017   0.5389   0.9130
   1.750   0.6987   0.01164   0.00503  -0.1026   0.5227   1.0000
   2.000   0.7284   0.01189   0.00513  -0.1032   0.5081   1.0000
   2.250   0.7575   0.01216   0.00523  -0.1036   0.4943   1.0000
   2.500   0.7860   0.01244   0.00534  -0.1038   0.4808   1.0000
   2.750   0.8142   0.01269   0.00550  -0.1040   0.4672   1.0000
   3.000   0.8421   0.01297   0.00569  -0.1041   0.4553   1.0000
   3.250   0.8698   0.01331   0.00586  -0.1041   0.4448   1.0000
   3.500   0.8971   0.01356   0.00607  -0.1040   0.4332   1.0000
   3.750   0.9240   0.01386   0.00628  -0.1039   0.4219   1.0000
   4.000   0.9505   0.01420   0.00647  -0.1037   0.4114   1.0000
   4.250   0.9772   0.01443   0.00671  -0.1035   0.4011   1.0000
   4.500   1.0037   0.01480   0.00696  -0.1033   0.3927   1.0000
   4.750   1.0298   0.01501   0.00719  -0.1030   0.3823   1.0000
   5.000   1.0554   0.01532   0.00742  -0.1027   0.3726   1.0000
   5.250   1.0811   0.01558   0.00767  -0.1023   0.3634   1.0000
   5.500   1.1069   0.01592   0.00796  -0.1020   0.3562   1.0000
   5.750   1.1325   0.01617   0.00825  -0.1016   0.3482   1.0000
   6.000   1.1575   0.01654   0.00853  -0.1012   0.3409   1.0000
   6.250   1.1826   0.01677   0.00884  -0.1008   0.3323   1.0000
   6.500   1.2066   0.01712   0.00911  -0.1002   0.3241   1.0000
   6.750   1.2310   0.01735   0.00942  -0.0996   0.3148   1.0000
   7.000   1.2545   0.01773   0.00973  -0.0990   0.3076   1.0000
   7.250   1.2789   0.01799   0.01009  -0.0985   0.2995   1.0000
   7.500   1.3014   0.01838   0.01042  -0.0977   0.2918   1.0000
   7.750   1.3250   0.01865   0.01078  -0.0970   0.2826   1.0000
   8.000   1.3466   0.01905   0.01115  -0.0961   0.2743   1.0000
   8.250   1.3690   0.01938   0.01153  -0.0953   0.2643   1.0000
   8.500   1.3902   0.01978   0.01195  -0.0944   0.2550   1.0000
   8.750   1.4104   0.02022   0.01238  -0.0933   0.2455   1.0000
   9.000   1.4311   0.02065   0.01284  -0.0923   0.2354   1.0000
   9.250   1.4499   0.02116   0.01336  -0.0910   0.2257   1.0000
   9.500   1.4679   0.02169   0.01390  -0.0896   0.2155   1.0000
   9.750   1.4847   0.02223   0.01446  -0.0881   0.2054   1.0000
  10.000   1.4988   0.02291   0.01512  -0.0862   0.1925   1.0000
  10.250   1.5119   0.02369   0.01588  -0.0843   0.1795   1.0000
  10.500   1.5236   0.02457   0.01673  -0.0823   0.1656   1.0000
  10.750   1.5333   0.02561   0.01773  -0.0802   0.1502   1.0000
  11.000   1.5399   0.02690   0.01896  -0.0780   0.1326   1.0000
  11.250   1.5428   0.02851   0.02048  -0.0756   0.1132   1.0000
  11.500   1.5441   0.03034   0.02227  -0.0733   0.0995   1.0000
  11.750   1.5448   0.03233   0.02423  -0.0713   0.0902   1.0000
  12.000   1.5472   0.03428   0.02623  -0.0696   0.0835   1.0000
  12.250   1.5485   0.03644   0.02844  -0.0682   0.0776   1.0000
  12.500   1.5527   0.03842   0.03051  -0.0670   0.0707   1.0000
  12.750   1.5545   0.04073   0.03291  -0.0660   0.0597   1.0000
  13.000   1.5470   0.04410   0.03625  -0.0651   0.0517   1.0000
  13.250   1.5413   0.04746   0.03966  -0.0646   0.0493   1.0000
  13.500   1.5357   0.05098   0.04325  -0.0644   0.0477   1.0000
  13.750   1.5287   0.05479   0.04718  -0.0644   0.0468   1.0000
  14.000   1.5202   0.05894   0.05146  -0.0646   0.0461   1.0000
  14.250   1.5104   0.06341   0.05606  -0.0652   0.0456   1.0000
  14.500   1.4988   0.06826   0.06106  -0.0660   0.0451   1.0000
  14.750   1.4860   0.07346   0.06640  -0.0670   0.0447   1.0000
  15.000   1.4721   0.07894   0.07202  -0.0683   0.0443   1.0000
  15.250   1.4579   0.08459   0.07780  -0.0697   0.0440   1.0000
  15.500   1.4435   0.09038   0.08373  -0.0713   0.0437   1.0000
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