Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.54 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b540ols-il-1000000-n5.txt
Download as CSV file: xf-b540ols-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -1.3645   0.08939   0.08635   0.0175   1.0000   0.0119
 -17.000  -1.4147   0.07730   0.07407   0.0109   1.0000   0.0118
 -16.750  -1.4609   0.06600   0.06258   0.0045   1.0000   0.0117
 -16.500  -1.4971   0.05606   0.05245  -0.0017   1.0000   0.0117
 -16.250  -1.5205   0.04755   0.04375  -0.0080   1.0000   0.0117
 -16.000  -1.5327   0.04088   0.03689  -0.0138   1.0000   0.0118
 -15.750  -1.5391   0.03634   0.03220  -0.0172   1.0000   0.0118
 -15.500  -1.5424   0.03338   0.02911  -0.0179   1.0000   0.0119
 -15.250  -1.5429   0.03138   0.02700  -0.0167   1.0000   0.0121
 -15.000  -1.5386   0.02989   0.02541  -0.0150   1.0000   0.0122
 -14.750  -1.5278   0.02857   0.02399  -0.0139   1.0000   0.0123
 -14.500  -1.5142   0.02739   0.02271  -0.0129   1.0000   0.0125
 -14.250  -1.4988   0.02630   0.02154  -0.0120   1.0000   0.0126
 -14.000  -1.4818   0.02530   0.02044  -0.0112   1.0000   0.0128
 -13.750  -1.4636   0.02436   0.01943  -0.0105   1.0000   0.0130
 -13.500  -1.4443   0.02349   0.01847  -0.0098   1.0000   0.0132
 -13.250  -1.4240   0.02268   0.01757  -0.0091   1.0000   0.0133
 -13.000  -1.4029   0.02193   0.01674  -0.0085   1.0000   0.0135
 -12.750  -1.3820   0.02109   0.01582  -0.0079   1.0000   0.0137
 -12.500  -1.3605   0.02027   0.01494  -0.0074   1.0000   0.0141
 -12.250  -1.3379   0.01958   0.01420  -0.0069   1.0000   0.0144
 -12.000  -1.3146   0.01895   0.01353  -0.0065   1.0000   0.0148
 -11.750  -1.2908   0.01836   0.01289  -0.0061   1.0000   0.0152
 -11.500  -1.2667   0.01780   0.01228  -0.0057   1.0000   0.0156
 -11.250  -1.2421   0.01727   0.01169  -0.0053   1.0000   0.0159
 -11.000  -1.2172   0.01677   0.01113  -0.0050   1.0000   0.0163
 -10.750  -1.1920   0.01630   0.01060  -0.0047   1.0000   0.0166
 -10.500  -1.1671   0.01574   0.01000  -0.0044   1.0000   0.0171
 -10.250  -1.1416   0.01524   0.00948  -0.0041   1.0000   0.0178
 -10.000  -1.1158   0.01480   0.00900  -0.0038   1.0000   0.0184
  -9.750  -1.0897   0.01438   0.00856  -0.0036   1.0000   0.0190
  -9.500  -1.0633   0.01400   0.00814  -0.0034   1.0000   0.0196
  -9.250  -1.0367   0.01365   0.00774  -0.0032   1.0000   0.0202
  -9.000  -1.0103   0.01322   0.00730  -0.0030   1.0000   0.0212
  -8.750  -0.9835   0.01285   0.00692  -0.0028   1.0000   0.0222
  -8.500  -0.9565   0.01252   0.00657  -0.0026   1.0000   0.0233
  -8.250  -0.9292   0.01222   0.00625  -0.0025   1.0000   0.0242
  -8.000  -0.9021   0.01186   0.00589  -0.0023   1.0000   0.0256
  -7.750  -0.8748   0.01155   0.00557  -0.0022   1.0000   0.0271
  -7.500  -0.8472   0.01127   0.00528  -0.0021   1.0000   0.0284
  -7.250  -0.8196   0.01099   0.00499  -0.0020   1.0000   0.0300
  -7.000  -0.7920   0.01070   0.00471  -0.0019   1.0000   0.0320
  -6.750  -0.7641   0.01045   0.00445  -0.0018   1.0000   0.0338
  -6.500  -0.7363   0.01018   0.00420  -0.0017   1.0000   0.0364
  -6.250  -0.7083   0.00993   0.00396  -0.0016   1.0000   0.0394
  -6.000  -0.6803   0.00969   0.00373  -0.0016   1.0000   0.0426
  -5.750  -0.6522   0.00944   0.00351  -0.0015   1.0000   0.0466
  -5.500  -0.6241   0.00921   0.00331  -0.0014   1.0000   0.0506
  -5.250  -0.5959   0.00899   0.00311  -0.0014   1.0000   0.0558
  -5.000  -0.5676   0.00875   0.00292  -0.0013   1.0000   0.0618
  -4.750  -0.5393   0.00856   0.00275  -0.0013   1.0000   0.0677
  -4.500  -0.5110   0.00833   0.00258  -0.0012   1.0000   0.0758
  -4.250  -0.4826   0.00811   0.00242  -0.0012   1.0000   0.0855
  -4.000  -0.4488   0.00792   0.00228  -0.0024   0.9630   0.0980
  -3.750  -0.4229   0.00786   0.00217  -0.0015   0.9009   0.1110
  -3.500  -0.3986   0.00789   0.00203  -0.0004   0.8296   0.1242
  -3.250  -0.3720   0.00794   0.00189   0.0001   0.7543   0.1398
  -3.000  -0.3444   0.00799   0.00177   0.0002   0.6820   0.1553
  -2.750  -0.3162   0.00798   0.00166   0.0003   0.6298   0.1728
  -2.500  -0.2878   0.00795   0.00156   0.0003   0.5840   0.1925
  -2.250  -0.2593   0.00792   0.00147   0.0002   0.5425   0.2139
  -2.000  -0.2307   0.00787   0.00140   0.0002   0.5134   0.2337
  -1.750  -0.2019   0.00781   0.00134   0.0002   0.4925   0.2531
  -1.500  -0.1733   0.00774   0.00129   0.0001   0.4709   0.2765
  -1.250  -0.1445   0.00769   0.00125   0.0001   0.4515   0.2968
  -1.000  -0.1156   0.00766   0.00122   0.0001   0.4369   0.3133
  -0.750  -0.0867   0.00761   0.00120   0.0001   0.4238   0.3326
  -0.500  -0.0579   0.00757   0.00119   0.0000   0.4107   0.3535
  -0.250  -0.0290   0.00756   0.00118   0.0000   0.3971   0.3694
   0.000   0.0000   0.00756   0.00118   0.0000   0.3828   0.3827
   0.250   0.0290   0.00756   0.00118   0.0000   0.3694   0.3969
   0.500   0.0579   0.00757   0.00119   0.0000   0.3534   0.4107
   0.750   0.0867   0.00761   0.00120  -0.0001   0.3325   0.4239
   1.000   0.1156   0.00766   0.00122  -0.0001   0.3134   0.4369
   1.250   0.1445   0.00769   0.00125  -0.0001   0.2970   0.4514
   1.500   0.1732   0.00773   0.00129  -0.0001   0.2765   0.4709
   1.750   0.2019   0.00781   0.00134  -0.0002   0.2530   0.4925
   2.000   0.2307   0.00787   0.00140  -0.0002   0.2336   0.5134
   2.250   0.2593   0.00792   0.00147  -0.0002   0.2134   0.5428
   2.500   0.2878   0.00795   0.00156  -0.0003   0.1930   0.5846
   2.750   0.3162   0.00798   0.00166  -0.0003   0.1730   0.6298
   3.000   0.3444   0.00799   0.00177  -0.0003   0.1550   0.6818
   3.250   0.3721   0.00794   0.00189  -0.0001   0.1398   0.7534
   3.500   0.3986   0.00789   0.00203   0.0004   0.1243   0.8295
   3.750   0.4229   0.00786   0.00217   0.0016   0.1110   0.9015
   4.000   0.4488   0.00792   0.00228   0.0024   0.0980   0.9630
   4.250   0.4826   0.00812   0.00242   0.0012   0.0853   1.0000
   4.500   0.5110   0.00834   0.00258   0.0012   0.0757   1.0000
   4.750   0.5393   0.00856   0.00275   0.0013   0.0677   1.0000
   5.000   0.5676   0.00875   0.00292   0.0013   0.0618   1.0000
   5.250   0.5959   0.00899   0.00311   0.0014   0.0557   1.0000
   5.500   0.6241   0.00921   0.00331   0.0014   0.0506   1.0000
   5.750   0.6523   0.00944   0.00351   0.0015   0.0467   1.0000
   6.000   0.6803   0.00968   0.00373   0.0016   0.0427   1.0000
   6.250   0.7084   0.00993   0.00396   0.0016   0.0393   1.0000
   6.500   0.7363   0.01018   0.00420   0.0017   0.0364   1.0000
   6.750   0.7642   0.01045   0.00445   0.0018   0.0338   1.0000
   7.000   0.7920   0.01070   0.00471   0.0019   0.0320   1.0000
   7.250   0.8197   0.01099   0.00499   0.0020   0.0300   1.0000
   7.500   0.8473   0.01127   0.00528   0.0021   0.0284   1.0000
   7.750   0.8748   0.01155   0.00557   0.0022   0.0271   1.0000
   8.000   0.9022   0.01186   0.00589   0.0023   0.0256   1.0000
   8.250   0.9293   0.01222   0.00625   0.0025   0.0242   1.0000
   8.500   0.9566   0.01252   0.00657   0.0026   0.0233   1.0000
   8.750   0.9836   0.01285   0.00692   0.0028   0.0222   1.0000
   9.000   1.0104   0.01322   0.00730   0.0030   0.0212   1.0000
   9.250   1.0368   0.01364   0.00774   0.0032   0.0202   1.0000
   9.500   1.0634   0.01400   0.00814   0.0034   0.0196   1.0000
   9.750   1.0898   0.01438   0.00856   0.0036   0.0190   1.0000
  10.000   1.1159   0.01480   0.00900   0.0038   0.0184   1.0000
  10.250   1.1418   0.01524   0.00948   0.0040   0.0178   1.0000
  10.500   1.1672   0.01573   0.01000   0.0043   0.0172   1.0000
  10.750   1.1921   0.01630   0.01061   0.0046   0.0166   1.0000
  11.000   1.2174   0.01677   0.01113   0.0050   0.0163   1.0000
  11.250   1.2423   0.01727   0.01169   0.0053   0.0159   1.0000
  11.500   1.2669   0.01780   0.01228   0.0056   0.0156   1.0000
  11.750   1.2910   0.01837   0.01289   0.0060   0.0152   1.0000
  12.000   1.3148   0.01895   0.01353   0.0064   0.0148   1.0000
  12.250   1.3381   0.01958   0.01420   0.0069   0.0144   1.0000
  12.500   1.3608   0.02027   0.01494   0.0073   0.0141   1.0000
  12.750   1.3822   0.02109   0.01582   0.0079   0.0137   1.0000
  13.000   1.4031   0.02193   0.01674   0.0085   0.0135   1.0000
  13.250   1.4243   0.02269   0.01757   0.0091   0.0133   1.0000
  13.500   1.4446   0.02350   0.01847   0.0097   0.0132   1.0000
  13.750   1.4639   0.02437   0.01943   0.0104   0.0130   1.0000
  14.000   1.4822   0.02530   0.02045   0.0111   0.0128   1.0000
  14.250   1.4992   0.02630   0.02154   0.0119   0.0126   1.0000
  14.500   1.5147   0.02739   0.02272   0.0128   0.0125   1.0000
  14.750   1.5283   0.02858   0.02399   0.0138   0.0123   1.0000
  15.000   1.5393   0.02989   0.02541   0.0149   0.0122   1.0000
  15.250   1.5438   0.03137   0.02699   0.0165   0.0120   1.0000
  15.500   1.5436   0.03335   0.02908   0.0177   0.0119   1.0000
  15.750   1.5407   0.03626   0.03212   0.0170   0.0118   1.0000
  16.000   1.5342   0.04082   0.03683   0.0137   0.0117   1.0000
  16.250   1.5220   0.04752   0.04371   0.0078   0.0117   1.0000
  16.500   1.4997   0.05587   0.05226   0.0016   0.0117   1.0000
  16.750   1.4634   0.06585   0.06243  -0.0047   0.0117   1.0000
  17.000   1.4176   0.07712   0.07389  -0.0111   0.0118   1.0000
  17.250   1.3670   0.08928   0.08623  -0.0178   0.0119   1.0000
<< Back to BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il)

Polar data table (+)

Polar graphs


<< Back to BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il)