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USA 49 AIRFOIL (usa49-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 49 AIRFOIL (usa49-il)
Reynolds number: 500,000
Max Cl/Cd: 65.6 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa49-il-500000-n5.txt
Download as CSV file: xf-usa49-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 49 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4524   0.08192   0.07986  -0.0070   1.0000   0.0060
  -8.500  -0.4561   0.07716   0.07512  -0.0085   1.0000   0.0058
  -8.000  -0.4669   0.06711   0.06511  -0.0123   1.0000   0.0056
  -7.500  -0.4869   0.05615   0.05421  -0.0198   1.0000   0.0053
  -6.500  -0.5270   0.03742   0.03450  -0.0326   1.0000   0.0046
  -6.250  -0.5119   0.03412   0.03095  -0.0327   1.0000   0.0049
  -6.000  -0.4940   0.03220   0.02887  -0.0323   1.0000   0.0052
  -5.750  -0.4779   0.02877   0.02513  -0.0313   1.0000   0.0055
  -5.500  -0.4627   0.02453   0.02041  -0.0295   1.0000   0.0054
  -5.250  -0.4351   0.02035   0.01564  -0.0298   0.9970   0.0052
  -5.000  -0.4033   0.01765   0.01247  -0.0308   0.9936   0.0052
  -4.750  -0.3723   0.01581   0.01032  -0.0315   0.9901   0.0054
  -4.500  -0.3408   0.01437   0.00863  -0.0323   0.9871   0.0057
  -4.250  -0.3108   0.01321   0.00728  -0.0327   0.9828   0.0062
  -4.000  -0.2797   0.01226   0.00620  -0.0333   0.9788   0.0067
  -3.750  -0.2495   0.01158   0.00542  -0.0338   0.9739   0.0074
  -3.500  -0.2199   0.01073   0.00451  -0.0343   0.9685   0.0084
  -3.250  -0.1907   0.01016   0.00388  -0.0346   0.9625   0.0092
  -3.000  -0.1616   0.00969   0.00334  -0.0348   0.9557   0.0104
  -2.750  -0.1336   0.00936   0.00295  -0.0347   0.9480   0.0117
  -2.500  -0.1058   0.00898   0.00245  -0.0345   0.9400   0.0144
  -2.250  -0.0789   0.00871   0.00211  -0.0342   0.9301   0.0186
  -2.000  -0.0528   0.00824   0.00183  -0.0338   0.9193   0.0715
  -1.750  -0.0270   0.00797   0.00168  -0.0333   0.9038   0.1192
  -1.500  -0.0016   0.00774   0.00152  -0.0326   0.8837   0.1590
  -1.250   0.0239   0.00745   0.00137  -0.0321   0.8606   0.2229
  -1.000   0.0481   0.00672   0.00124  -0.0317   0.8386   0.4213
  -0.750   0.0719   0.00610   0.00115  -0.0310   0.8134   0.6098
  -0.500   0.0969   0.00591   0.00108  -0.0303   0.7839   0.6892
  -0.250   0.1212   0.00574   0.00104  -0.0293   0.7508   0.7615
   0.000   0.1427   0.00570   0.00106  -0.0276   0.7018   0.8539
   0.250   0.1652   0.00579   0.00106  -0.0260   0.6499   0.9149
   0.500   0.1968   0.00602   0.00107  -0.0266   0.5904   0.9607
   0.750   0.2332   0.00631   0.00108  -0.0286   0.5323   0.9863
   1.000   0.2709   0.00651   0.00111  -0.0309   0.4972   1.0000
   1.250   0.2967   0.00669   0.00113  -0.0306   0.4630   1.0000
   1.500   0.3223   0.00694   0.00117  -0.0303   0.4154   1.0000
   1.750   0.3477   0.00727   0.00124  -0.0300   0.3554   1.0000
   2.000   0.3732   0.00765   0.00135  -0.0297   0.2969   1.0000
   2.250   0.3988   0.00803   0.00149  -0.0295   0.2416   1.0000
   2.500   0.4242   0.00848   0.00166  -0.0293   0.1800   1.0000
   2.750   0.4486   0.00922   0.00196  -0.0291   0.0746   1.0000
   3.000   0.4751   0.00948   0.00217  -0.0289   0.0615   1.0000
   3.250   0.5019   0.00967   0.00235  -0.0288   0.0576   1.0000
   3.500   0.5287   0.00989   0.00257  -0.0286   0.0542   1.0000
   3.750   0.5554   0.01014   0.00284  -0.0285   0.0513   1.0000
   4.000   0.5821   0.01037   0.00311  -0.0283   0.0499   1.0000
   4.250   0.6089   0.01060   0.00338  -0.0282   0.0489   1.0000
   4.500   0.6355   0.01085   0.00367  -0.0281   0.0478   1.0000
   4.750   0.6620   0.01114   0.00402  -0.0279   0.0466   1.0000
   5.000   0.6884   0.01146   0.00440  -0.0277   0.0455   1.0000
   5.250   0.7146   0.01177   0.00476  -0.0275   0.0440   1.0000
   5.500   0.7408   0.01208   0.00507  -0.0274   0.0410   1.0000
   5.750   0.7673   0.01230   0.00532  -0.0273   0.0379   1.0000
   6.000   0.7944   0.01240   0.00548  -0.0273   0.0344   1.0000
   6.250   0.8210   0.01259   0.00564  -0.0272   0.0298   1.0000
   6.500   0.8469   0.01291   0.00587  -0.0271   0.0150   1.0000
   6.750   0.8720   0.01345   0.00646  -0.0267   0.0099   1.0000
   7.000   0.8961   0.01413   0.00722  -0.0262   0.0081   1.0000
   7.250   0.9200   0.01485   0.00805  -0.0257   0.0067   1.0000
   7.500   0.9442   0.01547   0.00880  -0.0253   0.0059   1.0000
   7.750   0.9677   0.01619   0.00962  -0.0248   0.0053   1.0000
   8.000   0.9900   0.01711   0.01065  -0.0241   0.0048   1.0000
   8.250   1.0112   0.01822   0.01191  -0.0233   0.0045   1.0000
   8.500   1.0329   0.01921   0.01306  -0.0225   0.0042   1.0000
   8.750   1.0534   0.02037   0.01439  -0.0216   0.0040   1.0000
   9.000   1.0735   0.02157   0.01575  -0.0206   0.0037   1.0000
   9.250   1.0936   0.02265   0.01697  -0.0198   0.0034   1.0000
   9.500   1.1135   0.02365   0.01808  -0.0191   0.0032   1.0000
   9.750   1.1306   0.02507   0.01963  -0.0181   0.0030   1.0000
  10.000   1.1432   0.02719   0.02201  -0.0165   0.0028   1.0000
  10.250   1.1572   0.02900   0.02413  -0.0152   0.0027   1.0000
  10.500   1.1681   0.03111   0.02652  -0.0136   0.0027   1.0000
  10.750   1.1752   0.03354   0.02927  -0.0117   0.0026   1.0000
  11.000   1.1774   0.03629   0.03234  -0.0096   0.0025   1.0000
  11.250   1.1724   0.03916   0.03550  -0.0069   0.0024   1.0000
  11.500   1.1618   0.04233   0.03893  -0.0045   0.0024   1.0000
  11.750   1.1481   0.04620   0.04305  -0.0036   0.0024   1.0000
  12.000   1.1324   0.05102   0.04812  -0.0047   0.0024   1.0000
  12.250   1.1154   0.05717   0.05449  -0.0081   0.0024   1.0000
  12.500   1.0974   0.06486   0.06239  -0.0138   0.0024   1.0000
  12.750   1.0780   0.07386   0.07156  -0.0206   0.0024   1.0000
  13.000   1.0567   0.08401   0.08184  -0.0276   0.0025   1.0000
  13.250   1.0333   0.09502   0.09294  -0.0342   0.0025   1.0000
  13.500   1.0074   0.10651   0.10448  -0.0400   0.0026   1.0000
  13.750   0.9796   0.11853   0.11649  -0.0453   0.0027   1.0000
  14.000   0.9518   0.13070   0.12866  -0.0503   0.0028   1.0000
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