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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 100,000
Max Cl/Cd: 50.08 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40-il-100000.txt
Download as CSV file: xf-usa40-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2872   0.09644   0.09162  -0.0319   1.0000   0.1427
  -7.750  -0.3340   0.09707   0.09247  -0.0298   1.0000   0.1456
  -7.500  -0.3872   0.09761   0.09321  -0.0284   1.0000   0.1463
  -7.250  -0.3827   0.09409   0.08975  -0.0247   1.0000   0.1476
  -7.000  -0.3624   0.09156   0.08723  -0.0203   1.0000   0.1498
  -6.750  -0.3683   0.09035   0.08609  -0.0170   1.0000   0.1520
  -6.500  -0.3810   0.08927   0.08510  -0.0145   1.0000   0.1548
  -6.250  -0.3876   0.08364   0.07951  -0.0300   0.9931   0.1639
  -6.000  -0.3472   0.07901   0.07475  -0.0435   0.9828   0.1787
  -5.750  -0.3208   0.07500   0.07081  -0.0420   0.9757   0.1817
  -5.500  -0.2831   0.07220   0.06800  -0.0432   0.9701   0.1875
  -5.250  -0.2324   0.04064   0.03432  -0.0884   0.9574   0.1045
  -5.000  -0.1908   0.03682   0.02998  -0.0930   0.9483   0.1017
  -4.750  -0.1412   0.03340   0.02600  -0.0985   0.9422   0.1019
  -4.500  -0.1011   0.03088   0.02305  -0.1016   0.9325   0.1020
  -4.250  -0.0505   0.02866   0.02033  -0.1059   0.9263   0.1030
  -4.000  -0.0123   0.02674   0.01835  -0.1082   0.9165   0.1061
  -3.750   0.0371   0.02536   0.01687  -0.1119   0.9101   0.1124
  -3.500   0.0778   0.02404   0.01534  -0.1139   0.9004   0.1178
  -3.250   0.1226   0.02273   0.01412  -0.1165   0.8931   0.1272
  -3.000   0.1581   0.02179   0.01327  -0.1174   0.8820   0.1404
  -2.750   0.2009   0.02070   0.01224  -0.1194   0.8742   0.1634
  -2.500   0.2322   0.02000   0.01169  -0.1195   0.8611   0.1972
  -2.250   0.2672   0.01879   0.01091  -0.1204   0.8508   0.2709
  -2.000   0.2995   0.01785   0.01048  -0.1206   0.8390   0.3757
  -1.750   0.3264   0.01728   0.01028  -0.1198   0.8248   0.4646
  -1.500   0.3525   0.01685   0.01022  -0.1182   0.8112   0.5624
  -1.250   0.3778   0.01664   0.01018  -0.1161   0.7983   0.6492
  -1.000   0.4010   0.01657   0.01014  -0.1135   0.7841   0.7144
  -0.750   0.4201   0.01656   0.01013  -0.1102   0.7682   0.7684
  -0.500   0.4365   0.01641   0.00998  -0.1062   0.7524   0.8158
  -0.250   0.4526   0.01612   0.00966  -0.1024   0.7367   0.8598
   0.000   0.4706   0.01574   0.00924  -0.0990   0.7210   0.9043
   0.250   0.5085   0.01537   0.00877  -0.0998   0.7034   0.9625
   0.500   0.5456   0.01538   0.00854  -0.1018   0.6851   1.0000
   0.750   0.5769   0.01553   0.00846  -0.1026   0.6675   1.0000
   1.000   0.6077   0.01573   0.00844  -0.1033   0.6501   1.0000
   1.250   0.6379   0.01597   0.00847  -0.1038   0.6333   1.0000
   1.500   0.6678   0.01625   0.00854  -0.1042   0.6173   1.0000
   1.750   0.6976   0.01653   0.00862  -0.1045   0.6023   1.0000
   2.000   0.7265   0.01684   0.00876  -0.1047   0.5875   1.0000
   2.250   0.7543   0.01719   0.00900  -0.1047   0.5727   1.0000
   2.500   0.7821   0.01755   0.00925  -0.1047   0.5592   1.0000
   2.750   0.8107   0.01790   0.00944  -0.1048   0.5474   1.0000
   3.000   0.8387   0.01826   0.00968  -0.1048   0.5354   1.0000
   3.250   0.8655   0.01868   0.01006  -0.1046   0.5237   1.0000
   3.500   0.8941   0.01906   0.01027  -0.1047   0.5139   1.0000
   3.750   0.9205   0.01949   0.01070  -0.1045   0.5029   1.0000
   4.000   0.9478   0.01995   0.01108  -0.1044   0.4935   1.0000
   4.250   0.9750   0.02036   0.01142  -0.1042   0.4837   1.0000
   4.500   1.0010   0.02086   0.01191  -0.1039   0.4740   1.0000
   4.750   1.0287   0.02128   0.01221  -0.1038   0.4652   1.0000
   5.000   1.0535   0.02182   0.01280  -0.1034   0.4555   1.0000
   5.250   1.0818   0.02218   0.01299  -0.1033   0.4463   1.0000
   5.500   1.1046   0.02263   0.01352  -0.1025   0.4350   1.0000
   5.750   1.1305   0.02301   0.01380  -0.1021   0.4248   1.0000
   6.000   1.1551   0.02336   0.01414  -0.1016   0.4144   1.0000
   6.250   1.1792   0.02385   0.01465  -0.1010   0.4050   1.0000
   6.500   1.2048   0.02419   0.01490  -0.1005   0.3956   1.0000
   6.750   1.2272   0.02470   0.01550  -0.0997   0.3864   1.0000
   7.000   1.2528   0.02505   0.01578  -0.0993   0.3780   1.0000
   7.250   1.2750   0.02562   0.01647  -0.0985   0.3700   1.0000
   7.500   1.2991   0.02604   0.01689  -0.0980   0.3623   1.0000
   7.750   1.3217   0.02653   0.01743  -0.0972   0.3543   1.0000
   8.000   1.3438   0.02688   0.01783  -0.0963   0.3457   1.0000
   8.250   1.3655   0.02731   0.01830  -0.0954   0.3376   1.0000
   8.500   1.3863   0.02768   0.01873  -0.0944   0.3290   1.0000
   8.750   1.4075   0.02812   0.01920  -0.0934   0.3215   1.0000
   9.000   1.4266   0.02859   0.01981  -0.0922   0.3137   1.0000
   9.250   1.4477   0.02895   0.02014  -0.0912   0.3063   1.0000
   9.500   1.4635   0.02948   0.02086  -0.0895   0.2979   1.0000
   9.750   1.4848   0.02983   0.02115  -0.0886   0.2914   1.0000
  10.000   1.4978   0.03050   0.02207  -0.0866   0.2835   1.0000
  10.250   1.5152   0.03090   0.02248  -0.0852   0.2766   1.0000
  10.500   1.5274   0.03161   0.02339  -0.0831   0.2692   1.0000
  10.750   1.5410   0.03219   0.02406  -0.0813   0.2626   1.0000
  11.000   1.5510   0.03288   0.02486  -0.0790   0.2557   1.0000
  11.250   1.5583   0.03366   0.02579  -0.0764   0.2487   1.0000
  11.500   1.5670   0.03443   0.02661  -0.0741   0.2425   1.0000
  11.750   1.5713   0.03555   0.02794  -0.0716   0.2352   1.0000
  12.000   1.5771   0.03654   0.02895  -0.0694   0.2287   1.0000
  12.250   1.5790   0.03804   0.03069  -0.0672   0.2208   1.0000
  12.500   1.5807   0.03950   0.03220  -0.0652   0.2134   1.0000
  12.750   1.5791   0.04149   0.03440  -0.0635   0.2038   1.0000
  13.000   1.5766   0.04371   0.03673  -0.0620   0.1948   1.0000
  13.250   1.5709   0.04636   0.03945  -0.0608   0.1852   1.0000
  13.500   1.5635   0.04955   0.04279  -0.0601   0.1744   1.0000
  13.750   1.5524   0.05334   0.04670  -0.0597   0.1633   1.0000
  14.000   1.5376   0.05783   0.05127  -0.0598   0.1523   1.0000
  14.250   1.5189   0.06308   0.05658  -0.0605   0.1422   1.0000
  14.500   1.4970   0.06906   0.06263  -0.0616   0.1328   1.0000
  14.750   1.4739   0.07557   0.06922  -0.0632   0.1243   1.0000
  15.000   1.4491   0.08258   0.07628  -0.0652   0.1178   1.0000
  15.250   1.4252   0.08969   0.08343  -0.0673   0.1112   1.0000
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