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BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il)
Reynolds number: 50,000
Max Cl/Cd: 21.27 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b540ols-il-50000.txt
Download as CSV file: xf-b540ols-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BELL 540 AIRFOIL (MODIFIED NACA 0012)           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6663   0.11302   0.10568   0.0453   1.0000   0.3281
  -8.500  -0.7694   0.08126   0.07400   0.0071   1.0000   0.1726
  -8.250  -0.7697   0.07464   0.06730   0.0042   1.0000   0.1696
  -8.000  -0.7758   0.06713   0.05964   0.0002   1.0000   0.1673
  -7.750  -0.7822   0.05919   0.05137  -0.0038   1.0000   0.1657
  -7.500  -0.7810   0.05229   0.04398  -0.0064   1.0000   0.1662
  -7.250  -0.7728   0.04640   0.03745  -0.0079   1.0000   0.1687
  -7.000  -0.7561   0.04261   0.03330  -0.0080   1.0000   0.1751
  -6.750  -0.7358   0.03962   0.03000  -0.0079   1.0000   0.1832
  -6.500  -0.7141   0.03698   0.02714  -0.0076   1.0000   0.1930
  -6.250  -0.6918   0.03431   0.02410  -0.0074   1.0000   0.2051
  -6.000  -0.6679   0.03235   0.02200  -0.0069   1.0000   0.2203
  -5.750  -0.6434   0.03069   0.02031  -0.0062   1.0000   0.2377
  -5.500  -0.6187   0.02924   0.01882  -0.0055   1.0000   0.2594
  -5.250  -0.5940   0.02793   0.01754  -0.0047   1.0000   0.2845
  -5.000  -0.5693   0.02683   0.01646  -0.0038   1.0000   0.3140
  -4.750  -0.5447   0.02596   0.01567  -0.0027   1.0000   0.3460
  -4.500  -0.5205   0.02521   0.01505  -0.0014   1.0000   0.3801
  -4.250  -0.4964   0.02445   0.01441   0.0000   1.0000   0.4158
  -4.000  -0.4725   0.02365   0.01372   0.0014   1.0000   0.4521
  -3.750  -0.4486   0.02286   0.01298   0.0028   1.0000   0.4889
  -3.500  -0.4247   0.02208   0.01228   0.0041   1.0000   0.5256
  -3.250  -0.4011   0.02136   0.01170   0.0058   1.0000   0.5603
  -3.000  -0.3777   0.02066   0.01113   0.0075   1.0000   0.5951
  -2.750  -0.3549   0.02001   0.01060   0.0094   1.0000   0.6301
  -2.500  -0.3323   0.01939   0.01011   0.0114   1.0000   0.6660
  -2.250  -0.3099   0.01880   0.00964   0.0134   1.0000   0.7034
  -2.000  -0.2883   0.01824   0.00922   0.0157   1.0000   0.7430
  -1.750  -0.2675   0.01773   0.00890   0.0185   1.0000   0.7847
  -1.500  -0.2447   0.01728   0.00863   0.0210   1.0000   0.8333
  -1.250  -0.2063   0.01697   0.00842   0.0207   1.0000   0.8946
  -1.000  -0.1066   0.01685   0.00815   0.0077   1.0000   0.9690
  -0.750  -0.0472   0.01593   0.00714  -0.0020   1.0000   1.0000
  -0.500  -0.0372   0.01542   0.00656  -0.0013   1.0000   1.0000
  -0.250  -0.0197   0.01525   0.00632  -0.0006   1.0000   1.0000
   0.000   0.0000   0.01521   0.00625   0.0000   1.0000   1.0000
   0.250   0.0197   0.01525   0.00632   0.0006   1.0000   1.0000
   0.500   0.0372   0.01542   0.00656   0.0013   1.0000   1.0000
   0.750   0.0472   0.01593   0.00714   0.0020   1.0000   1.0000
   1.000   0.1065   0.01685   0.00815  -0.0077   0.9691   1.0000
   1.250   0.2063   0.01697   0.00842  -0.0207   0.8947   1.0000
   1.500   0.2448   0.01728   0.00863  -0.0210   0.8333   1.0000
   1.750   0.2675   0.01773   0.00890  -0.0185   0.7847   1.0000
   2.000   0.2883   0.01824   0.00922  -0.0157   0.7430   1.0000
   2.250   0.3100   0.01880   0.00964  -0.0134   0.7035   1.0000
   2.500   0.3324   0.01939   0.01011  -0.0114   0.6660   1.0000
   2.750   0.3550   0.02001   0.01060  -0.0094   0.6301   1.0000
   3.000   0.3778   0.02066   0.01113  -0.0076   0.5951   1.0000
   3.250   0.4012   0.02136   0.01170  -0.0058   0.5603   1.0000
   3.500   0.4247   0.02208   0.01228  -0.0042   0.5256   1.0000
   3.750   0.4486   0.02286   0.01298  -0.0028   0.4890   1.0000
   4.000   0.4726   0.02365   0.01372  -0.0014   0.4522   1.0000
   4.250   0.4965   0.02445   0.01441   0.0000   0.4158   1.0000
   4.500   0.5205   0.02521   0.01505   0.0014   0.3801   1.0000
   4.750   0.5448   0.02596   0.01567   0.0027   0.3461   1.0000
   5.000   0.5693   0.02683   0.01646   0.0038   0.3140   1.0000
   5.250   0.5941   0.02793   0.01754   0.0047   0.2845   1.0000
   5.500   0.6188   0.02924   0.01882   0.0055   0.2594   1.0000
   5.750   0.6434   0.03069   0.02031   0.0062   0.2378   1.0000
   6.000   0.6680   0.03235   0.02200   0.0068   0.2203   1.0000
   6.250   0.6919   0.03431   0.02410   0.0073   0.2051   1.0000
   6.500   0.7142   0.03698   0.02714   0.0076   0.1930   1.0000
   6.750   0.7359   0.03962   0.03000   0.0079   0.1832   1.0000
   7.000   0.7561   0.04261   0.03330   0.0080   0.1751   1.0000
   7.250   0.7729   0.04640   0.03745   0.0078   0.1687   1.0000
   7.500   0.7811   0.05229   0.04398   0.0063   0.1662   1.0000
   7.750   0.7823   0.05920   0.05138   0.0038   0.1657   1.0000
   8.000   0.7760   0.06713   0.05964  -0.0002   0.1673   1.0000
   8.250   0.7699   0.07465   0.06730  -0.0042   0.1696   1.0000
   8.500   0.7697   0.08127   0.07400  -0.0072   0.1726   1.0000
   8.750   0.6677   0.11311   0.10577  -0.0454   0.3280   1.0000
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