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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 200,000
Max Cl/Cd: 69.22 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40-il-200000-n5.txt
Download as CSV file: xf-usa40-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3314   0.09286   0.08897  -0.0431   1.0000   0.0371
  -9.500  -0.3476   0.08668   0.08284  -0.0453   1.0000   0.0366
  -9.250  -0.5171   0.04032   0.03555  -0.0905   0.9808   0.0352
  -9.000  -0.4990   0.03414   0.02863  -0.0977   0.9721   0.0357
  -8.750  -0.4710   0.03223   0.02660  -0.1001   0.9668   0.0361
  -8.500  -0.4417   0.03062   0.02485  -0.1022   0.9611   0.0366
  -8.250  -0.4090   0.02882   0.02285  -0.1050   0.9571   0.0371
  -8.000  -0.3823   0.02708   0.02087  -0.1063   0.9494   0.0376
  -7.750  -0.3510   0.02538   0.01892  -0.1082   0.9440   0.0380
  -7.500  -0.3206   0.02389   0.01720  -0.1097   0.9379   0.0385
  -7.250  -0.2908   0.02258   0.01567  -0.1107   0.9303   0.0391
  -7.000  -0.2570   0.02133   0.01420  -0.1123   0.9251   0.0397
  -6.750  -0.2288   0.02034   0.01302  -0.1127   0.9150   0.0403
  -6.500  -0.1953   0.01936   0.01187  -0.1138   0.9061   0.0410
  -6.250  -0.1658   0.01861   0.01111  -0.1143   0.8930   0.0418
  -6.000  -0.1363   0.01801   0.01047  -0.1146   0.8801   0.0428
  -5.750  -0.1062   0.01742   0.00979  -0.1149   0.8689   0.0439
  -5.500  -0.0778   0.01683   0.00911  -0.1150   0.8562   0.0449
  -5.250  -0.0496   0.01627   0.00845  -0.1149   0.8432   0.0459
  -5.000  -0.0212   0.01575   0.00784  -0.1149   0.8301   0.0469
  -4.750   0.0069   0.01529   0.00735  -0.1148   0.8164   0.0481
  -4.500   0.0346   0.01492   0.00693  -0.1147   0.8018   0.0497
  -4.250   0.0625   0.01458   0.00651  -0.1145   0.7870   0.0517
  -4.000   0.0903   0.01427   0.00613  -0.1144   0.7723   0.0543
  -3.750   0.1182   0.01401   0.00581  -0.1143   0.7573   0.0575
  -3.500   0.1461   0.01375   0.00546  -0.1141   0.7421   0.0615
  -3.250   0.1738   0.01351   0.00516  -0.1139   0.7265   0.0665
  -3.000   0.2016   0.01328   0.00487  -0.1138   0.7109   0.0731
  -2.750   0.2294   0.01309   0.00461  -0.1136   0.6956   0.0820
  -2.500   0.2571   0.01290   0.00438  -0.1135   0.6808   0.0937
  -2.250   0.2847   0.01270   0.00419  -0.1133   0.6663   0.1107
  -1.750   0.3398   0.01236   0.00402  -0.1132   0.6371   0.1924
  -1.500   0.3674   0.01224   0.00395  -0.1131   0.6233   0.2306
  -1.250   0.3949   0.01212   0.00390  -0.1130   0.6092   0.2701
  -1.000   0.4222   0.01202   0.00388  -0.1128   0.5949   0.3150
  -0.750   0.4496   0.01192   0.00388  -0.1127   0.5801   0.3686
  -0.500   0.4768   0.01181   0.00391  -0.1125   0.5655   0.4297
  -0.250   0.5034   0.01170   0.00399  -0.1121   0.5502   0.5036
   0.000   0.5294   0.01167   0.00411  -0.1115   0.5345   0.5756
   0.250   0.5551   0.01173   0.00423  -0.1108   0.5191   0.6341
   0.500   0.5809   0.01185   0.00434  -0.1101   0.5038   0.6751
   0.750   0.6066   0.01198   0.00444  -0.1094   0.4886   0.7048
   1.000   0.6327   0.01213   0.00453  -0.1088   0.4741   0.7269
   1.250   0.6586   0.01230   0.00463  -0.1082   0.4603   0.7455
   1.500   0.6843   0.01248   0.00473  -0.1076   0.4473   0.7626
   1.750   0.7097   0.01266   0.00484  -0.1069   0.4345   0.7798
   2.000   0.7353   0.01281   0.00495  -0.1063   0.4225   0.7973
   2.250   0.7603   0.01297   0.00507  -0.1056   0.4121   0.8146
   2.500   0.7854   0.01310   0.00519  -0.1049   0.4023   0.8328
   2.750   0.8103   0.01324   0.00530  -0.1041   0.3931   0.8537
   3.000   0.8344   0.01333   0.00540  -0.1032   0.3826   0.8808
   3.250   0.8620   0.01335   0.00546  -0.1029   0.3714   1.0000
   3.500   0.8887   0.01365   0.00563  -0.1028   0.3605   1.0000
   3.750   0.9160   0.01389   0.00582  -0.1028   0.3496   1.0000
   4.000   0.9425   0.01417   0.00602  -0.1026   0.3400   1.0000
   4.250   0.9690   0.01444   0.00623  -0.1024   0.3296   1.0000
   4.500   0.9953   0.01472   0.00645  -0.1022   0.3202   1.0000
   4.750   1.0212   0.01502   0.00669  -0.1019   0.3111   1.0000
   5.000   1.0472   0.01530   0.00694  -0.1017   0.3024   1.0000
   5.250   1.0724   0.01562   0.00720  -0.1013   0.2932   1.0000
   5.500   1.0980   0.01591   0.00748  -0.1010   0.2839   1.0000
   5.750   1.1225   0.01627   0.00777  -0.1005   0.2742   1.0000
   6.000   1.1476   0.01658   0.00808  -0.1001   0.2645   1.0000
   6.250   1.1718   0.01694   0.00840  -0.0996   0.2560   1.0000
   6.500   1.1956   0.01732   0.00874  -0.0990   0.2450   1.0000
   6.750   1.2192   0.01770   0.00911  -0.0984   0.2346   1.0000
   7.000   1.2418   0.01814   0.00950  -0.0977   0.2230   1.0000
   7.250   1.2634   0.01865   0.00993  -0.0968   0.2081   1.0000
   7.500   1.2838   0.01923   0.01042  -0.0959   0.1906   1.0000
   7.750   1.3028   0.01989   0.01099  -0.0947   0.1715   1.0000
   8.000   1.3196   0.02071   0.01166  -0.0933   0.1478   1.0000
   8.250   1.3251   0.02235   0.01292  -0.0906   0.0993   1.0000
   8.500   1.3382   0.02323   0.01374  -0.0886   0.0902   1.0000
   8.750   1.3522   0.02404   0.01455  -0.0868   0.0849   1.0000
   9.000   1.3674   0.02477   0.01532  -0.0852   0.0807   1.0000
   9.250   1.3808   0.02563   0.01620  -0.0834   0.0767   1.0000
   9.500   1.3960   0.02636   0.01699  -0.0819   0.0723   1.0000
   9.750   1.4101   0.02719   0.01787  -0.0804   0.0644   1.0000
  10.000   1.4094   0.02910   0.01963  -0.0777   0.0401   1.0000
  10.250   1.4159   0.03056   0.02114  -0.0758   0.0383   1.0000
  10.500   1.4230   0.03204   0.02269  -0.0742   0.0372   1.0000
  10.750   1.4307   0.03353   0.02428  -0.0727   0.0365   1.0000
  11.000   1.4371   0.03519   0.02605  -0.0714   0.0359   1.0000
  11.250   1.4422   0.03705   0.02802  -0.0702   0.0354   1.0000
  11.500   1.4455   0.03917   0.03026  -0.0691   0.0349   1.0000
  11.750   1.4466   0.04161   0.03282  -0.0682   0.0343   1.0000
  12.000   1.4459   0.04437   0.03570  -0.0676   0.0339   1.0000
  12.250   1.4428   0.04751   0.03897  -0.0671   0.0335   1.0000
  12.500   1.4416   0.05057   0.04217  -0.0669   0.0332   1.0000
  12.750   1.4393   0.05387   0.04561  -0.0669   0.0329   1.0000
  13.000   1.4351   0.05750   0.04937  -0.0671   0.0326   1.0000
  13.250   1.4295   0.06142   0.05344  -0.0675   0.0324   1.0000
  13.500   1.4224   0.06567   0.05782  -0.0681   0.0321   1.0000
  13.750   1.4141   0.07019   0.06248  -0.0689   0.0320   1.0000
  14.000   1.4048   0.07499   0.06742  -0.0700   0.0318   1.0000
  14.250   1.3948   0.08000   0.07256  -0.0711   0.0316   1.0000
  14.500   1.3844   0.08517   0.07785  -0.0725   0.0314   1.0000
  14.750   1.3738   0.09044   0.08325  -0.0739   0.0312   1.0000
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