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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.22 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51dtip-il-1000000.txt
Download as CSV file: xf-p51dtip-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4688   0.09276   0.09057  -0.0231   0.7723   0.0086
 -10.750  -0.4818   0.08474   0.08257  -0.0267   0.7716   0.0084
  -9.750  -0.8314   0.02802   0.02411  -0.0381   0.7710   0.0061
  -9.500  -0.8209   0.02530   0.02105  -0.0366   0.7688   0.0063
  -9.250  -0.8044   0.02350   0.01900  -0.0357   0.7665   0.0064
  -9.000  -0.7861   0.02191   0.01714  -0.0348   0.7645   0.0065
  -8.750  -0.7735   0.01870   0.01345  -0.0332   0.7626   0.0068
  -8.500  -0.7546   0.01698   0.01147  -0.0323   0.7606   0.0072
  -8.250  -0.7316   0.01616   0.01055  -0.0318   0.7588   0.0076
  -8.000  -0.7075   0.01553   0.00985  -0.0316   0.7572   0.0080
  -7.750  -0.6828   0.01502   0.00927  -0.0314   0.7554   0.0086
  -7.500  -0.6575   0.01460   0.00879  -0.0312   0.7535   0.0092
  -7.250  -0.6312   0.01436   0.00850  -0.0312   0.7517   0.0098
  -7.000  -0.6102   0.01312   0.00710  -0.0303   0.7500   0.0110
  -6.750  -0.5836   0.01294   0.00693  -0.0304   0.7482   0.0122
  -6.500  -0.5571   0.01274   0.00668  -0.0304   0.7463   0.0134
  -6.250  -0.5293   0.01270   0.00662  -0.0305   0.7448   0.0143
  -6.000  -0.5053   0.01201   0.00591  -0.0302   0.7433   0.0168
  -5.750  -0.4775   0.01195   0.00586  -0.0304   0.7418   0.0186
  -5.500  -0.4490   0.01201   0.00590  -0.0307   0.7402   0.0202
  -5.250  -0.4236   0.01154   0.00538  -0.0306   0.7387   0.0218
  -5.000  -0.3987   0.01098   0.00479  -0.0303   0.7372   0.0241
  -4.750  -0.3718   0.01077   0.00457  -0.0304   0.7357   0.0259
  -4.500  -0.3449   0.01055   0.00430  -0.0305   0.7344   0.0276
  -4.250  -0.3179   0.01035   0.00406  -0.0305   0.7329   0.0290
  -4.000  -0.2905   0.01023   0.00392  -0.0306   0.7314   0.0298
  -3.750  -0.2647   0.00975   0.00337  -0.0305   0.7302   0.0316
  -3.500  -0.2379   0.00941   0.00300  -0.0305   0.7288   0.0343
  -3.250  -0.2105   0.00919   0.00275  -0.0306   0.7273   0.0360
  -3.000  -0.1829   0.00900   0.00255  -0.0307   0.7259   0.0380
  -2.750  -0.1552   0.00884   0.00237  -0.0309   0.7246   0.0405
  -2.500  -0.1279   0.00859   0.00217  -0.0309   0.7234   0.0585
  -2.250  -0.1045   0.00769   0.00190  -0.0308   0.7221   0.2357
  -2.000  -0.0839   0.00630   0.00149  -0.0305   0.7209   0.5145
  -1.750  -0.0586   0.00593   0.00153  -0.0303   0.7197   0.6606
  -1.500  -0.0302   0.00598   0.00158  -0.0304   0.7185   0.6800
  -1.250  -0.0017   0.00607   0.00167  -0.0306   0.7173   0.6954
  -1.000   0.0269   0.00611   0.00172  -0.0308   0.7164   0.7053
  -0.750   0.0557   0.00618   0.00179  -0.0311   0.7154   0.7134
  -0.500   0.0841   0.00623   0.00187  -0.0312   0.7143   0.7223
  -0.250   0.1128   0.00633   0.00196  -0.0314   0.7131   0.7296
   0.000   0.1413   0.00632   0.00198  -0.0317   0.7117   0.7340
   0.250   0.1701   0.00633   0.00199  -0.0320   0.7101   0.7366
   0.500   0.1990   0.00634   0.00200  -0.0323   0.7085   0.7388
   0.750   0.2279   0.00635   0.00200  -0.0326   0.7071   0.7402
   1.000   0.2569   0.00637   0.00201  -0.0330   0.7057   0.7414
   1.250   0.2857   0.00642   0.00205  -0.0333   0.7033   0.7428
   1.500   0.3145   0.00635   0.00200  -0.0336   0.6994   0.7441
   1.750   0.3429   0.00619   0.00182  -0.0337   0.6909   0.7456
   2.000   0.3713   0.00605   0.00170  -0.0338   0.6809   0.7468
   2.250   0.3998   0.00600   0.00167  -0.0340   0.6732   0.7479
   2.500   0.4286   0.00597   0.00168  -0.0343   0.6678   0.7490
   2.750   0.4570   0.00596   0.00168  -0.0345   0.6607   0.7502
   3.000   0.4856   0.00594   0.00170  -0.0348   0.6505   0.7515
   3.250   0.5137   0.00595   0.00170  -0.0349   0.6334   0.7528
   3.500   0.5407   0.00606   0.00171  -0.0349   0.5879   0.7541
   3.750   0.5527   0.00792   0.00246  -0.0330   0.3197   0.7556
   4.000   0.5723   0.00887   0.00290  -0.0322   0.1962   0.7570
   4.250   0.5929   0.00967   0.00330  -0.0315   0.1051   0.7582
   4.500   0.6138   0.01035   0.00369  -0.0307   0.0426   0.7600
   4.750   0.6391   0.01061   0.00396  -0.0305   0.0365   0.7615
   5.000   0.6639   0.01092   0.00427  -0.0302   0.0318   0.7631
   5.250   0.6886   0.01123   0.00464  -0.0299   0.0289   0.7648
   5.500   0.7142   0.01143   0.00488  -0.0297   0.0271   0.7666
   5.750   0.7390   0.01171   0.00515  -0.0295   0.0235   0.7686
   6.000   0.7626   0.01209   0.00555  -0.0290   0.0193   0.7706
   6.250   0.7876   0.01233   0.00576  -0.0288   0.0159   0.7725
   6.500   0.8092   0.01283   0.00632  -0.0279   0.0130   0.7748
   6.750   0.8326   0.01316   0.00669  -0.0274   0.0116   0.7770
   7.000   0.8546   0.01361   0.00716  -0.0267   0.0103   0.7794
   7.250   0.8706   0.01459   0.00826  -0.0250   0.0092   0.7821
   7.500   0.8927   0.01502   0.00873  -0.0242   0.0088   0.7847
   7.750   0.9140   0.01549   0.00925  -0.0234   0.0081   0.7874
   8.000   0.9342   0.01600   0.00984  -0.0225   0.0076   0.7904
   8.250   0.9535   0.01660   0.01051  -0.0214   0.0071   0.7938
   8.500   0.9723   0.01726   0.01122  -0.0203   0.0068   0.7973
   8.750   0.9886   0.01820   0.01225  -0.0188   0.0065   0.8010
   9.000   1.0015   0.01982   0.01405  -0.0168   0.0062   0.8051
   9.250   1.0182   0.02165   0.01610  -0.0155   0.0060   0.8095
   9.500   1.0360   0.02275   0.01734  -0.0143   0.0059   0.8144
   9.750   1.0519   0.02331   0.01803  -0.0127   0.0057   0.8200
  10.000   1.0670   0.02471   0.01963  -0.0112   0.0056   0.8263
  10.250   1.0801   0.02568   0.02077  -0.0094   0.0053   0.8334
  10.500   1.0905   0.02746   0.02278  -0.0074   0.0052   0.8420
  10.750   1.0972   0.02931   0.02489  -0.0050   0.0050   0.8532
  11.000   1.0990   0.03150   0.02737  -0.0022   0.0049   0.8693
  11.250   1.0969   0.03326   0.02953   0.0012   0.0047   0.9197
  11.500   1.0691   0.04091   0.03792   0.0041   0.0049   1.0000
  11.750   1.0234   0.04866   0.04614   0.0081   0.0051   1.0000
  12.000   0.9871   0.05527   0.05303   0.0099   0.0053   1.0000
  12.250   0.9553   0.06157   0.05955   0.0102   0.0054   1.0000
  12.500   0.9251   0.06836   0.06652   0.0089   0.0055   1.0000
  12.750   0.8954   0.07604   0.07435   0.0060   0.0055   1.0000
  13.000   0.8708   0.08433   0.08276   0.0010   0.0056   1.0000
  13.250   0.8043   0.08376   0.08233  -0.0021   0.0054   1.0000
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