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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 1,000,000
Max Cl/Cd: 68.41 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51dtip-il-1000000-n5.txt
Download as CSV file: xf-p51dtip-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5626   0.14396   0.14152  -0.0031   0.7670   0.0028
 -12.750  -0.9697   0.04115   0.03825  -0.0504   0.7663   0.0023
 -12.250  -1.0066   0.03415   0.03077  -0.0447   0.7606   0.0023
 -12.000  -1.0123   0.03177   0.02818  -0.0417   0.7580   0.0023
 -11.750  -1.0083   0.02961   0.02580  -0.0398   0.7557   0.0024
 -11.500  -0.9980   0.02797   0.02399  -0.0384   0.7534   0.0025
 -11.250  -0.9853   0.02646   0.02229  -0.0372   0.7513   0.0025
 -10.750  -0.9543   0.02371   0.01920  -0.0353   0.7475   0.0027
 -10.500  -0.9374   0.02229   0.01758  -0.0344   0.7455   0.0028
 -10.250  -0.9181   0.02119   0.01632  -0.0337   0.7434   0.0029
 -10.000  -0.8975   0.02023   0.01522  -0.0331   0.7413   0.0030
  -9.750  -0.8773   0.01910   0.01391  -0.0325   0.7393   0.0031
  -9.500  -0.8554   0.01826   0.01290  -0.0320   0.7374   0.0033
  -9.250  -0.8328   0.01749   0.01201  -0.0316   0.7357   0.0034
  -9.000  -0.8099   0.01673   0.01113  -0.0312   0.7342   0.0035
  -8.750  -0.7863   0.01607   0.01036  -0.0309   0.7326   0.0036
  -8.500  -0.7623   0.01546   0.00966  -0.0306   0.7309   0.0037
  -8.250  -0.7398   0.01456   0.00861  -0.0301   0.7292   0.0040
  -8.000  -0.7161   0.01388   0.00782  -0.0297   0.7275   0.0044
  -7.750  -0.6917   0.01335   0.00722  -0.0294   0.7258   0.0048
  -7.500  -0.6666   0.01294   0.00677  -0.0293   0.7241   0.0054
  -7.250  -0.6412   0.01256   0.00630  -0.0291   0.7224   0.0060
  -7.000  -0.6156   0.01221   0.00588  -0.0290   0.7209   0.0065
  -6.750  -0.5898   0.01185   0.00547  -0.0289   0.7194   0.0068
  -6.500  -0.5642   0.01141   0.00500  -0.0287   0.7179   0.0096
  -6.250  -0.5378   0.01115   0.00476  -0.0287   0.7163   0.0123
  -6.000  -0.5111   0.01092   0.00452  -0.0288   0.7148   0.0142
  -5.750  -0.4843   0.01068   0.00424  -0.0288   0.7133   0.0156
  -5.500  -0.4573   0.01050   0.00408  -0.0289   0.7119   0.0189
  -5.250  -0.4299   0.01036   0.00392  -0.0290   0.7105   0.0213
  -5.000  -0.4026   0.01021   0.00374  -0.0292   0.7092   0.0231
  -4.750  -0.3750   0.01011   0.00358  -0.0293   0.7079   0.0242
  -4.500  -0.3471   0.01004   0.00350  -0.0296   0.7067   0.0248
  -4.250  -0.3193   0.00993   0.00339  -0.0298   0.7054   0.0251
  -4.000  -0.2924   0.00965   0.00307  -0.0298   0.7039   0.0257
  -3.750  -0.2652   0.00940   0.00278  -0.0299   0.7025   0.0263
  -3.500  -0.2379   0.00919   0.00255  -0.0300   0.7010   0.0269
  -3.250  -0.2103   0.00901   0.00233  -0.0301   0.6997   0.0274
  -3.000  -0.1826   0.00885   0.00215  -0.0303   0.6984   0.0281
  -2.750  -0.1548   0.00870   0.00199  -0.0305   0.6972   0.0292
  -2.500  -0.1270   0.00857   0.00186  -0.0306   0.6960   0.0304
  -2.250  -0.0991   0.00846   0.00172  -0.0308   0.6949   0.0315
  -1.750  -0.0434   0.00815   0.00151  -0.0312   0.6928   0.0570
  -1.500  -0.0164   0.00781   0.00139  -0.0314   0.6917   0.1205
  -1.250   0.0085   0.00711   0.00121  -0.0315   0.6906   0.2816
  -1.000   0.0290   0.00567   0.00094  -0.0311   0.6894   0.6264
  -0.750   0.0573   0.00565   0.00098  -0.0313   0.6882   0.6616
  -0.500   0.0860   0.00566   0.00101  -0.0316   0.6871   0.6759
  -0.250   0.1148   0.00566   0.00103  -0.0318   0.6859   0.6827
   0.000   0.1436   0.00568   0.00104  -0.0321   0.6843   0.6888
   0.250   0.1724   0.00570   0.00104  -0.0324   0.6826   0.6936
   0.500   0.2010   0.00571   0.00107  -0.0327   0.6809   0.6981
   0.750   0.2299   0.00573   0.00109  -0.0330   0.6766   0.7051
   1.000   0.2585   0.00571   0.00109  -0.0332   0.6707   0.7079
   1.250   0.2870   0.00572   0.00109  -0.0335   0.6660   0.7105
   1.500   0.3158   0.00570   0.00110  -0.0338   0.6583   0.7120
   1.750   0.3443   0.00571   0.00110  -0.0340   0.6469   0.7135
   2.000   0.3726   0.00574   0.00109  -0.0342   0.6297   0.7149
   2.250   0.4002   0.00585   0.00110  -0.0343   0.5965   0.7160
   2.500   0.4173   0.00725   0.00163  -0.0331   0.3730   0.7172
   2.750   0.4422   0.00772   0.00186  -0.0330   0.3044   0.7184
   3.000   0.4655   0.00835   0.00214  -0.0327   0.2171   0.7195
   3.250   0.4896   0.00884   0.00239  -0.0324   0.1532   0.7205
   3.500   0.5142   0.00923   0.00262  -0.0322   0.1084   0.7217
   3.750   0.5389   0.00962   0.00286  -0.0320   0.0711   0.7228
   4.000   0.5633   0.01001   0.00313  -0.0317   0.0388   0.7240
   4.250   0.5892   0.01024   0.00335  -0.0316   0.0337   0.7252
   4.500   0.6152   0.01046   0.00358  -0.0315   0.0303   0.7265
   4.750   0.6410   0.01068   0.00380  -0.0314   0.0273   0.7279
   5.000   0.6665   0.01093   0.00405  -0.0312   0.0250   0.7293
   5.250   0.6920   0.01117   0.00431  -0.0311   0.0235   0.7307
   5.500   0.7181   0.01135   0.00454  -0.0310   0.0228   0.7321
   5.750   0.7437   0.01155   0.00476  -0.0309   0.0197   0.7335
   6.000   0.7680   0.01185   0.00503  -0.0306   0.0130   0.7351
   6.250   0.7919   0.01218   0.00534  -0.0302   0.0095   0.7368
   6.500   0.8151   0.01257   0.00578  -0.0296   0.0068   0.7387
   6.750   0.8387   0.01290   0.00616  -0.0291   0.0064   0.7406
   7.000   0.8619   0.01326   0.00656  -0.0286   0.0059   0.7425
   7.250   0.8846   0.01364   0.00698  -0.0280   0.0053   0.7445
   7.500   0.9067   0.01406   0.00743  -0.0274   0.0048   0.7465
   8.000   0.9479   0.01511   0.00859  -0.0256   0.0039   0.7506
   8.250   0.9650   0.01592   0.00957  -0.0241   0.0036   0.7531
   8.500   0.9854   0.01641   0.01013  -0.0232   0.0035   0.7557
   8.750   1.0045   0.01700   0.01080  -0.0221   0.0034   0.7584
   9.000   1.0226   0.01766   0.01154  -0.0209   0.0033   0.7611
   9.250   1.0401   0.01816   0.01211  -0.0195   0.0031   0.7639
   9.500   1.0551   0.01885   0.01291  -0.0177   0.0031   0.7672
   9.750   1.0702   0.01958   0.01373  -0.0161   0.0029   0.7709
  10.000   1.0851   0.02035   0.01460  -0.0145   0.0028   0.7748
  10.250   1.0998   0.02118   0.01554  -0.0130   0.0027   0.7788
  10.500   1.1152   0.02190   0.01634  -0.0116   0.0025   0.7836
  10.750   1.1288   0.02288   0.01745  -0.0101   0.0025   0.7885
  11.000   1.1415   0.02396   0.01869  -0.0086   0.0024   0.7934
  11.250   1.1546   0.02492   0.01977  -0.0072   0.0024   0.7993
  11.500   1.1688   0.02568   0.02060  -0.0061   0.0023   0.8053
  11.750   1.1806   0.02670   0.02173  -0.0047   0.0022   0.8126
  12.000   1.1912   0.02785   0.02300  -0.0033   0.0021   0.8204
  12.250   1.1966   0.02954   0.02488  -0.0015   0.0020   0.8301
  12.500   1.1987   0.03150   0.02706   0.0005   0.0020   0.8417
  12.750   1.1948   0.03405   0.02989   0.0028   0.0019   0.8570
  13.000   1.1902   0.03648   0.03262   0.0050   0.0019   0.8841
  13.250   1.1960   0.03933   0.03588   0.0042   0.0018   1.0000
  13.500   1.1956   0.04170   0.03840   0.0053   0.0018   1.0000
  13.750   1.1920   0.04444   0.04130   0.0063   0.0018   1.0000
  14.000   1.1895   0.04711   0.04411   0.0070   0.0018   1.0000
  14.250   1.1676   0.05220   0.04945   0.0076   0.0018   1.0000
  14.500   1.1512   0.05691   0.05434   0.0074   0.0018   1.0000
  14.750   1.1473   0.06025   0.05779   0.0069   0.0018   1.0000
  15.000   1.1187   0.06759   0.06536   0.0047   0.0018   1.0000
  15.250   1.0951   0.07522   0.07316   0.0012   0.0018   1.0000
  15.500   1.0541   0.08900   0.08718  -0.0074   0.0018   1.0000
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