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BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il)
Reynolds number: 100,000
Max Cl/Cd: 34.11 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b540ols-il-100000-n5.txt
Download as CSV file: xf-b540ols-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8884   0.09802   0.09253   0.0187   1.0000   0.0406
 -12.000  -0.9426   0.08118   0.07557   0.0064   1.0000   0.0398
 -11.750  -0.9841   0.06849   0.06264  -0.0049   1.0000   0.0393
 -11.500  -1.0136   0.06028   0.05414  -0.0121   1.0000   0.0391
 -11.250  -1.0357   0.05511   0.04868  -0.0139   1.0000   0.0392
 -11.000  -1.0483   0.05069   0.04386  -0.0141   1.0000   0.0397
 -10.750  -1.0532   0.04662   0.03927  -0.0139   1.0000   0.0405
 -10.500  -1.0435   0.04417   0.03667  -0.0134   1.0000   0.0415
 -10.250  -1.0297   0.04230   0.03470  -0.0129   1.0000   0.0426
 -10.000  -1.0157   0.04021   0.03241  -0.0124   1.0000   0.0438
  -9.750  -1.0009   0.03793   0.02983  -0.0118   1.0000   0.0451
  -9.500  -0.9846   0.03567   0.02722  -0.0112   1.0000   0.0467
  -9.250  -0.9664   0.03367   0.02490  -0.0106   1.0000   0.0486
  -9.000  -0.9459   0.03232   0.02356  -0.0102   1.0000   0.0505
  -8.750  -0.9248   0.03094   0.02205  -0.0097   1.0000   0.0527
  -8.500  -0.9031   0.02942   0.02030  -0.0092   1.0000   0.0551
  -8.250  -0.8810   0.02801   0.01872  -0.0087   1.0000   0.0578
  -8.000  -0.8583   0.02693   0.01764  -0.0083   1.0000   0.0608
  -7.750  -0.8348   0.02580   0.01636  -0.0078   1.0000   0.0644
  -7.500  -0.8113   0.02463   0.01510  -0.0073   1.0000   0.0680
  -7.250  -0.7875   0.02370   0.01416  -0.0069   1.0000   0.0725
  -7.000  -0.7627   0.02279   0.01308  -0.0064   1.0000   0.0778
  -6.750  -0.7387   0.02185   0.01219  -0.0061   1.0000   0.0835
  -6.500  -0.7136   0.02102   0.01129  -0.0057   1.0000   0.0907
  -6.250  -0.6886   0.02022   0.01051  -0.0054   1.0000   0.0990
  -6.000  -0.6634   0.01945   0.00975  -0.0051   1.0000   0.1089
  -5.750  -0.6377   0.01874   0.00905  -0.0048   1.0000   0.1208
  -5.500  -0.6119   0.01807   0.00842  -0.0046   1.0000   0.1355
  -5.250  -0.5858   0.01745   0.00784  -0.0043   1.0000   0.1531
  -5.000  -0.5595   0.01688   0.00732  -0.0041   1.0000   0.1742
  -4.750  -0.5333   0.01633   0.00689  -0.0039   1.0000   0.1976
  -4.500  -0.5067   0.01586   0.00649  -0.0037   1.0000   0.2232
  -4.250  -0.4800   0.01544   0.00616  -0.0035   1.0000   0.2507
  -4.000  -0.4533   0.01506   0.00589  -0.0032   1.0000   0.2784
  -3.750  -0.4266   0.01472   0.00564  -0.0030   1.0000   0.3059
  -3.500  -0.3996   0.01444   0.00543  -0.0027   1.0000   0.3326
  -3.250  -0.3726   0.01418   0.00525  -0.0024   1.0000   0.3580
  -3.000  -0.3456   0.01394   0.00507  -0.0021   1.0000   0.3824
  -2.750  -0.3187   0.01370   0.00491  -0.0018   1.0000   0.4061
  -2.500  -0.2917   0.01347   0.00474  -0.0014   1.0000   0.4288
  -2.250  -0.2650   0.01322   0.00460  -0.0010   1.0000   0.4503
  -2.000  -0.2382   0.01299   0.00447  -0.0007   1.0000   0.4726
  -1.750  -0.2116   0.01276   0.00437  -0.0003   1.0000   0.4956
  -1.500  -0.1852   0.01252   0.00428   0.0002   1.0000   0.5194
  -1.250  -0.1588   0.01230   0.00422   0.0007   1.0000   0.5455
  -1.000  -0.1331   0.01208   0.00419   0.0012   1.0000   0.5750
  -0.750  -0.1072   0.01185   0.00419   0.0018   0.9987   0.6101
  -0.500  -0.0648   0.01164   0.00423  -0.0008   0.9427   0.6598
  -0.250  -0.0270   0.01146   0.00426  -0.0018   0.8688   0.7207
   0.000   0.0000   0.01140   0.00426   0.0000   0.7907   0.7907
   0.250   0.0270   0.01146   0.00426   0.0018   0.7207   0.8689
   0.500   0.0648   0.01164   0.00423   0.0008   0.6598   0.9427
   0.750   0.1071   0.01185   0.00419  -0.0018   0.6102   0.9987
   1.000   0.1331   0.01208   0.00419  -0.0012   0.5750   1.0000
   1.250   0.1588   0.01230   0.00422  -0.0006   0.5455   1.0000
   1.500   0.1852   0.01252   0.00428  -0.0002   0.5194   1.0000
   1.750   0.2116   0.01276   0.00437   0.0003   0.4956   1.0000
   2.000   0.2382   0.01299   0.00447   0.0007   0.4726   1.0000
   2.250   0.2649   0.01322   0.00460   0.0011   0.4503   1.0000
   2.500   0.2916   0.01347   0.00474   0.0014   0.4288   1.0000
   2.750   0.3186   0.01370   0.00491   0.0018   0.4061   1.0000
   3.000   0.3456   0.01394   0.00507   0.0021   0.3825   1.0000
   3.250   0.3726   0.01418   0.00525   0.0024   0.3581   1.0000
   3.500   0.3996   0.01444   0.00543   0.0027   0.3326   1.0000
   3.750   0.4265   0.01472   0.00564   0.0030   0.3059   1.0000
   4.000   0.4533   0.01506   0.00589   0.0032   0.2784   1.0000
   4.250   0.4800   0.01544   0.00616   0.0035   0.2507   1.0000
   4.500   0.5067   0.01586   0.00649   0.0037   0.2232   1.0000
   4.750   0.5333   0.01633   0.00689   0.0039   0.1976   1.0000
   5.000   0.5595   0.01688   0.00732   0.0041   0.1742   1.0000
   5.250   0.5858   0.01745   0.00784   0.0043   0.1532   1.0000
   5.500   0.6119   0.01807   0.00842   0.0046   0.1355   1.0000
   5.750   0.6377   0.01874   0.00905   0.0048   0.1208   1.0000
   6.000   0.6634   0.01945   0.00975   0.0051   0.1089   1.0000
   6.250   0.6887   0.02022   0.01051   0.0054   0.0990   1.0000
   6.500   0.7136   0.02102   0.01129   0.0057   0.0907   1.0000
   6.750   0.7387   0.02185   0.01219   0.0061   0.0835   1.0000
   7.000   0.7627   0.02279   0.01308   0.0064   0.0778   1.0000
   7.250   0.7875   0.02370   0.01416   0.0069   0.0725   1.0000
   7.500   0.8114   0.02463   0.01510   0.0073   0.0679   1.0000
   7.750   0.8349   0.02580   0.01636   0.0078   0.0644   1.0000
   8.000   0.8583   0.02693   0.01764   0.0082   0.0608   1.0000
   8.250   0.8810   0.02801   0.01872   0.0086   0.0578   1.0000
   8.500   0.9032   0.02942   0.02030   0.0092   0.0551   1.0000
   8.750   0.9249   0.03094   0.02205   0.0097   0.0527   1.0000
   9.000   0.9460   0.03232   0.02356   0.0102   0.0505   1.0000
   9.250   0.9665   0.03367   0.02490   0.0106   0.0486   1.0000
   9.500   0.9847   0.03567   0.02723   0.0112   0.0467   1.0000
   9.750   1.0011   0.03793   0.02983   0.0118   0.0451   1.0000
  10.000   1.0159   0.04022   0.03242   0.0124   0.0438   1.0000
  10.250   1.0299   0.04231   0.03471   0.0129   0.0426   1.0000
  10.500   1.0437   0.04417   0.03667   0.0134   0.0415   1.0000
  10.750   1.0534   0.04664   0.03929   0.0139   0.0405   1.0000
  11.000   1.0485   0.05072   0.04388   0.0141   0.0397   1.0000
  11.250   1.0359   0.05515   0.04872   0.0138   0.0392   1.0000
  11.500   1.0139   0.06033   0.05420   0.0120   0.0391   1.0000
  11.750   0.9843   0.06861   0.06277   0.0047   0.0392   1.0000
  12.000   0.9425   0.08142   0.07582  -0.0067   0.0398   1.0000
  12.250   0.8879   0.09842   0.09294  -0.0192   0.0406   1.0000
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