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USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 5 AIRFOIL (usa5-il)
Reynolds number: 100,000
Max Cl/Cd: 55.83 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa5-il-100000.txt
Download as CSV file: xf-usa5-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 5 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3374   0.09301   0.08849  -0.0220   1.0000   0.0617
  -7.000  -0.3433   0.09136   0.08693  -0.0217   1.0000   0.0633
  -6.750  -0.3469   0.09009   0.08574  -0.0234   1.0000   0.0646
  -6.500  -0.3483   0.08956   0.08525  -0.0277   1.0000   0.0654
  -6.250  -0.3438   0.08840   0.08405  -0.0313   1.0000   0.0657
  -6.000  -0.3446   0.08216   0.07795  -0.0257   1.0000   0.0667
  -5.750  -0.3426   0.07870   0.07454  -0.0223   1.0000   0.0682
  -5.500  -0.3396   0.07605   0.07193  -0.0210   1.0000   0.0700
  -5.250  -0.3352   0.07349   0.06939  -0.0208   1.0000   0.0725
  -5.000  -0.3273   0.07109   0.06696  -0.0221   1.0000   0.0757
  -4.750  -0.3014   0.07054   0.06610  -0.0303   1.0000   0.0787
  -4.500  -0.3028   0.06557   0.06130  -0.0267   1.0000   0.0798
  -4.250  -0.2993   0.06241   0.05820  -0.0241   1.0000   0.0816
  -4.000  -0.2904   0.05991   0.05570  -0.0232   1.0000   0.0866
  -3.750  -0.2646   0.05764   0.05313  -0.0277   1.0000   0.0930
  -3.500  -0.2614   0.05433   0.04995  -0.0249   1.0000   0.0959
  -3.250  -0.2470   0.05189   0.04743  -0.0248   1.0000   0.1010
  -3.000  -0.2226   0.04956   0.04477  -0.0271   1.0000   0.1069
  -2.750  -0.1937   0.04589   0.04108  -0.0293   0.9951   0.1120
  -2.500  -0.1455   0.04227   0.03714  -0.0351   0.9864   0.1224
  -2.250  -0.1030   0.03917   0.03378  -0.0392   0.9781   0.1363
  -2.000  -0.0599   0.03660   0.03091  -0.0431   0.9700   0.1627
  -1.750  -0.0096   0.03111   0.02440  -0.0450   0.9627   0.0941
  -1.500   0.0344   0.02765   0.02038  -0.0472   0.9562   0.0857
  -1.250   0.0733   0.02545   0.01752  -0.0484   0.9463   0.0941
  -1.000   0.1162   0.02382   0.01541  -0.0506   0.9378   0.1069
  -0.750   0.1596   0.02232   0.01374  -0.0532   0.9289   0.1239
  -0.500   0.1989   0.02124   0.01245  -0.0550   0.9178   0.1488
  -0.250   0.2415   0.02017   0.01124  -0.0573   0.9078   0.1749
   0.000   0.2922   0.01906   0.01024  -0.0615   0.9003   0.2086
   0.250   0.3356   0.01814   0.00939  -0.0640   0.8887   0.2326
   0.500   0.3833   0.01726   0.00858  -0.0674   0.8773   0.2610
   0.750   0.4266   0.01634   0.00791  -0.0697   0.8645   0.3150
   1.000   0.5424   0.01404   0.00679  -0.0870   0.8586   1.0000
   1.250   0.5734   0.01376   0.00636  -0.0866   0.8355   1.0000
   1.500   0.6048   0.01346   0.00592  -0.0862   0.8098   1.0000
   1.750   0.6338   0.01327   0.00556  -0.0853   0.7801   1.0000
   2.000   0.6616   0.01319   0.00531  -0.0842   0.7477   1.0000
   2.250   0.6863   0.01329   0.00522  -0.0828   0.7117   1.0000
   2.500   0.7112   0.01350   0.00518  -0.0816   0.6785   1.0000
   2.750   0.7350   0.01381   0.00529  -0.0803   0.6472   1.0000
   3.000   0.7590   0.01418   0.00546  -0.0793   0.6208   1.0000
   3.250   0.7827   0.01457   0.00578  -0.0782   0.5977   1.0000
   3.500   0.8069   0.01496   0.00605  -0.0773   0.5786   1.0000
   3.750   0.8304   0.01534   0.00638  -0.0764   0.5599   1.0000
   4.000   0.8542   0.01572   0.00671  -0.0755   0.5434   1.0000
   4.250   0.8779   0.01610   0.00706  -0.0746   0.5282   1.0000
   4.500   0.9017   0.01649   0.00750  -0.0737   0.5141   1.0000
   4.750   0.9258   0.01691   0.00795  -0.0729   0.5015   1.0000
   5.000   0.9498   0.01735   0.00844  -0.0721   0.4895   1.0000
   5.250   0.9716   0.01767   0.00872  -0.0708   0.4704   1.0000
   5.500   0.9887   0.01785   0.00877  -0.0684   0.4391   1.0000
   5.750   1.0087   0.01818   0.00921  -0.0668   0.4178   1.0000
   6.000   1.0301   0.01858   0.00966  -0.0655   0.4008   1.0000
   6.250   1.0482   0.01886   0.01001  -0.0636   0.3757   1.0000
   6.500   1.0636   0.01908   0.01021  -0.0611   0.3426   1.0000
   6.750   1.0820   0.01938   0.01063  -0.0592   0.3152   1.0000
   7.000   1.0990   0.01970   0.01102  -0.0570   0.2682   1.0000
   7.250   1.1080   0.02096   0.01166  -0.0541   0.1721   1.0000
   7.500   1.1104   0.02355   0.01336  -0.0506   0.0602   1.0000
   7.750   1.1214   0.02514   0.01493  -0.0479   0.0467   1.0000
   8.000   1.1324   0.02661   0.01654  -0.0451   0.0425   1.0000
   8.250   1.1406   0.02817   0.01828  -0.0420   0.0405   1.0000
   8.500   1.1486   0.02959   0.01992  -0.0389   0.0395   1.0000
   8.750   1.1546   0.03111   0.02161  -0.0356   0.0388   1.0000
   9.000   1.1595   0.03273   0.02335  -0.0321   0.0383   1.0000
   9.250   1.1661   0.03443   0.02513  -0.0289   0.0381   1.0000
   9.500   1.1780   0.03632   0.02710  -0.0266   0.0370   1.0000
   9.750   1.1954   0.03841   0.02934  -0.0250   0.0357   1.0000
  10.000   1.2169   0.04089   0.03193  -0.0242   0.0344   1.0000
  10.250   1.2453   0.04411   0.03543  -0.0239   0.0353   1.0000
  10.500   1.2637   0.04775   0.03946  -0.0225   0.0366   1.0000
  10.750   1.2736   0.05145   0.04353  -0.0205   0.0380   1.0000
  11.000   1.2780   0.05561   0.04804  -0.0182   0.0393   1.0000
  11.250   1.2902   0.06213   0.05480  -0.0177   0.0411   1.0000
  11.500   1.2826   0.06241   0.05544  -0.0130   0.0424   1.0000
  11.750   1.2585   0.06485   0.05830  -0.0083   0.0435   1.0000
  12.000   1.2351   0.06810   0.06189  -0.0056   0.0441   1.0000
  12.250   1.2094   0.07236   0.06646  -0.0043   0.0449   1.0000
  12.500   1.1867   0.07696   0.07132  -0.0045   0.0453   1.0000
  12.750   1.1626   0.08233   0.07691  -0.0059   0.0457   1.0000
  13.000   1.1384   0.08834   0.08311  -0.0086   0.0458   1.0000
  13.250   1.1143   0.09502   0.08995  -0.0124   0.0457   1.0000
  13.500   1.0878   0.10297   0.09804  -0.0176   0.0455   1.0000
  13.750   1.0631   0.11147   0.10665  -0.0234   0.0452   1.0000
  14.000   1.0356   0.12164   0.11690  -0.0304   0.0450   1.0000
  14.250   1.0047   0.13436   0.12963  -0.0389   0.0452   1.0000
  14.500   0.9787   0.14831   0.14352  -0.0467   0.0472   1.0000
  14.750   0.9724   0.15595   0.15112  -0.0498   0.0498   1.0000
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