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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 500,000
Max Cl/Cd: 63.73 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51dtip-il-500000-n5.txt
Download as CSV file: xf-p51dtip-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: P-51D TIP (BL215) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5967   0.08263   0.07983  -0.0346   0.7785   0.0050
 -10.750  -0.6313   0.06987   0.06707  -0.0446   0.7766   0.0048
 -10.500  -0.7052   0.05652   0.05355  -0.0494   0.7737   0.0044
 -10.250  -0.7531   0.04961   0.04641  -0.0465   0.7705   0.0044
 -10.000  -0.8114   0.03666   0.03277  -0.0417   0.7680   0.0044
  -9.750  -0.8215   0.03044   0.02593  -0.0388   0.7658   0.0045
  -9.500  -0.8079   0.02843   0.02365  -0.0378   0.7639   0.0046
  -9.250  -0.7922   0.02654   0.02150  -0.0369   0.7619   0.0049
  -9.000  -0.7755   0.02456   0.01923  -0.0360   0.7597   0.0051
  -8.750  -0.7567   0.02281   0.01722  -0.0352   0.7575   0.0054
  -8.500  -0.7358   0.02148   0.01566  -0.0346   0.7554   0.0057
  -8.250  -0.7131   0.02055   0.01455  -0.0342   0.7535   0.0062
  -8.000  -0.6901   0.01961   0.01343  -0.0339   0.7518   0.0065
  -7.750  -0.6667   0.01873   0.01237  -0.0335   0.7503   0.0068
  -7.500  -0.6480   0.01666   0.00997  -0.0323   0.7487   0.0078
  -7.250  -0.6249   0.01575   0.00889  -0.0318   0.7470   0.0091
  -7.000  -0.6000   0.01526   0.00837  -0.0316   0.7452   0.0105
  -6.750  -0.5748   0.01482   0.00787  -0.0314   0.7434   0.0121
  -6.500  -0.5490   0.01450   0.00748  -0.0313   0.7416   0.0141
  -6.250  -0.5233   0.01416   0.00709  -0.0312   0.7399   0.0156
  -6.000  -0.4972   0.01388   0.00678  -0.0312   0.7382   0.0182
  -5.750  -0.4711   0.01361   0.00644  -0.0311   0.7367   0.0206
  -5.250  -0.4172   0.01329   0.00599  -0.0312   0.7339   0.0247
  -5.000  -0.3918   0.01286   0.00555  -0.0311   0.7323   0.0269
  -4.750  -0.3659   0.01250   0.00513  -0.0311   0.7308   0.0285
  -4.500  -0.3396   0.01219   0.00478  -0.0311   0.7292   0.0298
  -4.250  -0.3132   0.01191   0.00444  -0.0310   0.7278   0.0307
  -4.000  -0.2866   0.01163   0.00412  -0.0310   0.7264   0.0315
  -3.750  -0.2598   0.01139   0.00382  -0.0311   0.7251   0.0321
  -3.500  -0.2329   0.01116   0.00355  -0.0311   0.7238   0.0327
  -3.250  -0.2059   0.01095   0.00328  -0.0312   0.7226   0.0337
  -2.750  -0.1515   0.01054   0.00282  -0.0313   0.7200   0.0376
  -2.500  -0.1239   0.01037   0.00265  -0.0315   0.7185   0.0409
  -2.250  -0.0968   0.01012   0.00248  -0.0316   0.7171   0.0605
  -2.000  -0.0721   0.00947   0.00227  -0.0316   0.7158   0.1797
  -1.750  -0.0490   0.00853   0.00200  -0.0316   0.7145   0.3737
  -1.500  -0.0289   0.00747   0.00193  -0.0308   0.7132   0.6552
  -1.250  -0.0008   0.00752   0.00200  -0.0308   0.7121   0.6819
  -1.000   0.0273   0.00758   0.00207  -0.0309   0.7110   0.6980
  -0.750   0.0559   0.00764   0.00208  -0.0311   0.7100   0.7070
  -0.500   0.0843   0.00767   0.00212  -0.0313   0.7090   0.7127
  -0.250   0.1129   0.00774   0.00215  -0.0316   0.7081   0.7200
   0.000   0.1410   0.00780   0.00224  -0.0316   0.7072   0.7273
   0.250   0.1696   0.00786   0.00230  -0.0319   0.7060   0.7331
   0.500   0.1984   0.00787   0.00233  -0.0323   0.7047   0.7349
   0.750   0.2271   0.00788   0.00237  -0.0326   0.7034   0.7363
   1.000   0.2558   0.00789   0.00241  -0.0329   0.7018   0.7374
   1.250   0.2845   0.00789   0.00243  -0.0333   0.6998   0.7384
   1.500   0.3131   0.00785   0.00238  -0.0335   0.6959   0.7394
   1.750   0.3415   0.00779   0.00235  -0.0337   0.6900   0.7404
   2.000   0.3698   0.00771   0.00228  -0.0338   0.6819   0.7416
   2.250   0.3980   0.00763   0.00223  -0.0339   0.6713   0.7430
   2.500   0.4261   0.00757   0.00216  -0.0340   0.6568   0.7444
   2.750   0.4539   0.00754   0.00212  -0.0341   0.6387   0.7458
   3.000   0.4818   0.00756   0.00214  -0.0342   0.6166   0.7470
   3.250   0.4981   0.00866   0.00241  -0.0326   0.4170   0.7484
   3.500   0.5176   0.00960   0.00293  -0.0318   0.3056   0.7496
   3.750   0.5374   0.01046   0.00336  -0.0310   0.2009   0.7510
   4.000   0.5596   0.01104   0.00373  -0.0305   0.1398   0.7524
   4.250   0.5821   0.01156   0.00406  -0.0300   0.0938   0.7539
   4.500   0.6043   0.01210   0.00443  -0.0294   0.0526   0.7555
   4.750   0.6280   0.01248   0.00476  -0.0290   0.0408   0.7572
   5.000   0.6525   0.01279   0.00510  -0.0287   0.0365   0.7590
   5.250   0.6762   0.01316   0.00546  -0.0283   0.0322   0.7610
   5.500   0.7004   0.01345   0.00582  -0.0280   0.0290   0.7628
   5.750   0.7240   0.01376   0.00618  -0.0275   0.0261   0.7647
   6.000   0.7467   0.01415   0.00661  -0.0269   0.0234   0.7666
   6.250   0.7711   0.01438   0.00691  -0.0266   0.0203   0.7687
   6.500   0.7935   0.01477   0.00728  -0.0260   0.0141   0.7709
   6.750   0.8153   0.01520   0.00775  -0.0253   0.0115   0.7733
   7.000   0.8363   0.01571   0.00827  -0.0244   0.0096   0.7757
   7.250   0.8556   0.01633   0.00897  -0.0233   0.0082   0.7780
   7.500   0.8713   0.01726   0.01005  -0.0215   0.0072   0.7807
   7.750   0.8857   0.01834   0.01127  -0.0196   0.0068   0.7837
   8.000   0.9057   0.01885   0.01185  -0.0187   0.0064   0.7869
   8.250   0.9241   0.01945   0.01252  -0.0175   0.0060   0.7901
   8.500   0.9407   0.02012   0.01338  -0.0160   0.0055   0.7935
   8.750   0.9565   0.02102   0.01441  -0.0145   0.0053   0.7975
   9.000   0.9729   0.02200   0.01552  -0.0131   0.0050   0.8019
   9.250   0.9898   0.02279   0.01642  -0.0118   0.0047   0.8064
   9.500   1.0059   0.02381   0.01759  -0.0105   0.0045   0.8113
   9.750   1.0217   0.02481   0.01872  -0.0092   0.0044   0.8168
  10.000   1.0362   0.02594   0.02001  -0.0079   0.0042   0.8225
  10.250   1.0491   0.02733   0.02158  -0.0064   0.0040   0.8292
  10.500   1.0572   0.02954   0.02409  -0.0044   0.0038   0.8365
  10.750   1.0645   0.03156   0.02638  -0.0025   0.0037   0.8457
  11.000   1.0599   0.03511   0.03037   0.0004   0.0036   0.8571
  11.500   1.0545   0.04043   0.03643   0.0047   0.0035   0.9132
  11.750   1.0531   0.04395   0.04030   0.0048   0.0035   1.0000
  12.000   1.0398   0.04778   0.04437   0.0064   0.0035   1.0000
  12.250   1.0247   0.05193   0.04876   0.0075   0.0035   1.0000
  12.500   1.0086   0.05637   0.05342   0.0079   0.0035   1.0000
  12.750   0.9850   0.06205   0.05931   0.0075   0.0035   1.0000
  13.000   0.9636   0.06797   0.06542   0.0060   0.0035   1.0000
  13.250   0.9409   0.07490   0.07252   0.0030   0.0035   1.0000
  13.500   0.9153   0.08418   0.08198  -0.0024   0.0035   1.0000
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