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

P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.52 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51droot-il-1000000-n5.txt
Download as CSV file: xf-p51droot-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: P-51D ROOT (BL17.5) 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.2142   0.07513   0.07134  -0.0543   1.0000   0.0166
 -19.500  -1.2208   0.07091   0.06702  -0.0562   1.0000   0.0167
 -19.250  -1.2251   0.06709   0.06311  -0.0578   1.0000   0.0168
 -19.000  -1.2275   0.06361   0.05955  -0.0592   1.0000   0.0171
 -18.750  -1.2317   0.06001   0.05586  -0.0605   1.0000   0.0172
 -18.500  -1.2336   0.05678   0.05257  -0.0616   1.0000   0.0174
 -18.250  -1.2335   0.05388   0.04959  -0.0626   1.0000   0.0177
 -18.000  -1.2316   0.05124   0.04690  -0.0633   1.0000   0.0180
 -17.750  -1.2287   0.04882   0.04441  -0.0639   1.0000   0.0182
 -17.500  -1.2243   0.04659   0.04213  -0.0644   1.0000   0.0185
 -17.000  -1.2073   0.04233   0.03774  -0.0664   0.9689   0.0190
 -16.750  -1.1878   0.04043   0.03577  -0.0690   0.9634   0.0194
 -16.500  -1.1667   0.03853   0.03378  -0.0720   0.9572   0.0198
 -16.250  -1.1488   0.03658   0.03172  -0.0745   0.9494   0.0199
 -16.000  -1.1315   0.03519   0.03023  -0.0758   0.9396   0.0203
 -15.750  -1.1221   0.03374   0.02869  -0.0758   0.9320   0.0205
 -15.250  -1.1081   0.03083   0.02565  -0.0749   0.9217   0.0212
 -15.000  -1.0990   0.02959   0.02435  -0.0743   0.9178   0.0215
 -14.750  -1.0891   0.02845   0.02316  -0.0737   0.9142   0.0219
 -14.500  -1.0784   0.02740   0.02206  -0.0730   0.9107   0.0224
 -14.250  -1.0671   0.02637   0.02099  -0.0723   0.9078   0.0227
 -14.000  -1.0556   0.02538   0.01995  -0.0716   0.9048   0.0231
 -13.750  -1.0438   0.02444   0.01895  -0.0708   0.9018   0.0235
 -13.500  -1.0316   0.02354   0.01799  -0.0700   0.8992   0.0238
 -13.250  -1.0192   0.02268   0.01707  -0.0691   0.8967   0.0241
 -13.000  -1.0067   0.02183   0.01616  -0.0682   0.8944   0.0243
 -12.750  -0.9966   0.02085   0.01516  -0.0670   0.8917   0.0248
 -12.500  -0.9846   0.02003   0.01430  -0.0658   0.8891   0.0252
 -12.250  -0.9725   0.01926   0.01350  -0.0646   0.8864   0.0256
 -12.000  -0.9595   0.01859   0.01280  -0.0633   0.8836   0.0262
 -11.750  -0.9463   0.01798   0.01214  -0.0619   0.8809   0.0267
 -11.500  -0.9330   0.01739   0.01152  -0.0605   0.8785   0.0272
 -11.250  -0.9197   0.01682   0.01092  -0.0589   0.8759   0.0276
 -11.000  -0.9066   0.01630   0.01036  -0.0572   0.8728   0.0280
 -10.750  -0.8935   0.01583   0.00985  -0.0553   0.8696   0.0284
 -10.500  -0.8811   0.01540   0.00937  -0.0530   0.8662   0.0288
 -10.250  -0.8686   0.01502   0.00896  -0.0507   0.8633   0.0296
 -10.000  -0.8510   0.01464   0.00858  -0.0494   0.8603   0.0304
  -9.750  -0.8314   0.01429   0.00822  -0.0483   0.8567   0.0312
  -9.500  -0.8107   0.01397   0.00788  -0.0473   0.8533   0.0320
  -9.250  -0.7894   0.01366   0.00753  -0.0464   0.8498   0.0328
  -9.000  -0.7672   0.01338   0.00721  -0.0457   0.8458   0.0334
  -8.750  -0.7453   0.01303   0.00686  -0.0449   0.8402   0.0345
  -8.500  -0.7228   0.01272   0.00654  -0.0442   0.8333   0.0356
  -8.250  -0.6993   0.01244   0.00625  -0.0436   0.8253   0.0368
  -8.000  -0.6756   0.01219   0.00596  -0.0431   0.8135   0.0381
  -7.750  -0.6516   0.01198   0.00567  -0.0425   0.7926   0.0390
  -7.500  -0.6301   0.01180   0.00533  -0.0414   0.7440   0.0407
  -7.250  -0.6083   0.01177   0.00510  -0.0405   0.6896   0.0423
  -7.000  -0.5844   0.01167   0.00489  -0.0399   0.6619   0.0438
  -6.750  -0.5595   0.01156   0.00469  -0.0396   0.6428   0.0451
  -6.500  -0.5343   0.01142   0.00448  -0.0392   0.6286   0.0467
  -6.250  -0.5092   0.01124   0.00427  -0.0389   0.6167   0.0491
  -6.000  -0.4834   0.01108   0.00408  -0.0387   0.6072   0.0514
  -5.500  -0.4312   0.01078   0.00372  -0.0383   0.5907   0.0565
  -5.250  -0.4050   0.01062   0.00354  -0.0382   0.5835   0.0599
  -5.000  -0.3785   0.01047   0.00338  -0.0380   0.5778   0.0643
  -4.750  -0.3522   0.01027   0.00320  -0.0379   0.5728   0.0726
  -4.500  -0.3267   0.01001   0.00302  -0.0377   0.5678   0.0911
  -4.000  -0.2744   0.00956   0.00271  -0.0374   0.5595   0.1330
  -3.750  -0.2475   0.00938   0.00258  -0.0374   0.5558   0.1494
  -3.500  -0.2205   0.00920   0.00245  -0.0373   0.5521   0.1672
  -3.250  -0.1938   0.00902   0.00232  -0.0373   0.5485   0.1882
  -2.750  -0.1457   0.00800   0.00187  -0.0366   0.5425   0.3390
  -2.500  -0.1211   0.00751   0.00166  -0.0363   0.5398   0.4160
  -2.250  -0.0952   0.00719   0.00157  -0.0361   0.5368   0.4784
  -2.000  -0.0675   0.00710   0.00155  -0.0362   0.5337   0.5104
  -1.750  -0.0392   0.00708   0.00155  -0.0363   0.5303   0.5279
  -1.500  -0.0107   0.00709   0.00155  -0.0364   0.5269   0.5372
  -1.250   0.0184   0.00709   0.00155  -0.0366   0.5240   0.5461
  -1.000   0.0471   0.00709   0.00157  -0.0368   0.5209   0.5561
  -0.750   0.0761   0.00711   0.00158  -0.0370   0.5180   0.5621
  -0.500   0.1050   0.00714   0.00158  -0.0372   0.5153   0.5661
  -0.250   0.1335   0.00717   0.00161  -0.0373   0.5115   0.5719
   0.000   0.1624   0.00720   0.00163  -0.0375   0.5078   0.5769
   0.250   0.1915   0.00723   0.00165  -0.0377   0.5052   0.5820
   0.500   0.2202   0.00724   0.00168  -0.0379   0.5023   0.5869
   0.750   0.2488   0.00727   0.00171  -0.0380   0.4983   0.5900
   1.000   0.2773   0.00733   0.00174  -0.0381   0.4941   0.5926
   1.250   0.3062   0.00736   0.00177  -0.0383   0.4914   0.5949
   1.500   0.3352   0.00739   0.00179  -0.0386   0.4884   0.5971
   1.750   0.3641   0.00743   0.00182  -0.0388   0.4853   0.5986
   2.000   0.3926   0.00745   0.00186  -0.0389   0.4816   0.6005
   2.250   0.4207   0.00750   0.00190  -0.0390   0.4768   0.6022
   2.500   0.4494   0.00753   0.00194  -0.0392   0.4719   0.6039
   2.750   0.4779   0.00756   0.00199  -0.0393   0.4676   0.6056
   3.000   0.5062   0.00761   0.00204  -0.0394   0.4633   0.6076
   3.250   0.5343   0.00768   0.00210  -0.0395   0.4588   0.6095
   3.500   0.5628   0.00773   0.00216  -0.0396   0.4518   0.6114
   3.750   0.5904   0.00782   0.00223  -0.0396   0.4427   0.6131
   4.000   0.6181   0.00791   0.00230  -0.0396   0.4302   0.6146
   4.250   0.6441   0.00810   0.00239  -0.0394   0.4027   0.6160
   4.500   0.6567   0.00919   0.00290  -0.0371   0.2794   0.6178
   4.750   0.6796   0.00958   0.00316  -0.0364   0.2512   0.6197
   5.000   0.7032   0.00991   0.00339  -0.0358   0.2241   0.6216
   5.250   0.7224   0.01049   0.00371  -0.0346   0.1729   0.6236
   5.500   0.7452   0.01081   0.00395  -0.0338   0.1537   0.6258
   5.750   0.7693   0.01105   0.00416  -0.0333   0.1451   0.6281
   6.000   0.7938   0.01125   0.00435  -0.0328   0.1386   0.6302
   6.250   0.8174   0.01149   0.00457  -0.0322   0.1315   0.6321
   6.750   0.8644   0.01191   0.00499  -0.0309   0.1197   0.6360
   7.000   0.8861   0.01217   0.00523  -0.0300   0.1124   0.6383
   7.250   0.9083   0.01239   0.00546  -0.0291   0.1058   0.6407
   7.500   0.9282   0.01270   0.00573  -0.0279   0.0962   0.6432
   7.750   0.9450   0.01306   0.00602  -0.0261   0.0839   0.6457
   8.000   0.9582   0.01343   0.00635  -0.0237   0.0724   0.6482
   8.250   0.9718   0.01385   0.00672  -0.0214   0.0642   0.6507
   8.500   0.9857   0.01426   0.00713  -0.0192   0.0581   0.6538
   8.750   1.0012   0.01465   0.00753  -0.0174   0.0540   0.6570
   9.000   1.0156   0.01510   0.00799  -0.0154   0.0499   0.6602
   9.250   1.0316   0.01551   0.00841  -0.0138   0.0472   0.6634
   9.500   1.0465   0.01598   0.00889  -0.0120   0.0442   0.6665
   9.750   1.0612   0.01647   0.00939  -0.0103   0.0417   0.6698
  10.000   1.0761   0.01695   0.00990  -0.0087   0.0394   0.6738
  10.250   1.0905   0.01748   0.01045  -0.0070   0.0375   0.6780
  10.500   1.1044   0.01804   0.01104  -0.0054   0.0358   0.6826
  10.750   1.1193   0.01857   0.01162  -0.0039   0.0347   0.6876
  11.000   1.1330   0.01916   0.01225  -0.0023   0.0335   0.6941
  11.250   1.1460   0.01982   0.01294  -0.0007   0.0322   0.7008
  11.500   1.1581   0.02052   0.01369   0.0009   0.0311   0.7089
  11.750   1.1711   0.02121   0.01444   0.0024   0.0302   0.7188
  12.000   1.1837   0.02190   0.01523   0.0038   0.0296   0.7337
  12.250   1.1949   0.02264   0.01610   0.0054   0.0288   0.7594
  12.500   1.2018   0.02326   0.01702   0.0078   0.0282   0.8526
  12.750   1.2310   0.02411   0.01815   0.0054   0.0272   0.9489
  13.000   1.2511   0.02530   0.01938   0.0045   0.0263   1.0000
  13.250   1.2630   0.02634   0.02046   0.0054   0.0258   1.0000
  13.500   1.2749   0.02742   0.02158   0.0062   0.0252   1.0000
  13.750   1.2858   0.02862   0.02283   0.0070   0.0248   1.0000
  14.000   1.2966   0.02988   0.02412   0.0077   0.0243   1.0000
  14.250   1.3066   0.03123   0.02551   0.0083   0.0237   1.0000
  14.500   1.3159   0.03270   0.02701   0.0088   0.0232   1.0000
  14.750   1.3244   0.03428   0.02863   0.0093   0.0226   1.0000
  15.000   1.3316   0.03604   0.03043   0.0097   0.0221   1.0000
  15.250   1.3406   0.03765   0.03209   0.0101   0.0218   1.0000
  15.500   1.3502   0.03923   0.03373   0.0103   0.0215   1.0000
  15.750   1.3584   0.04097   0.03552   0.0105   0.0211   1.0000
  16.000   1.3663   0.04276   0.03737   0.0106   0.0207   1.0000
  16.250   1.3737   0.04462   0.03928   0.0107   0.0202   1.0000
  16.500   1.3805   0.04655   0.04125   0.0108   0.0198   1.0000
  16.750   1.3859   0.04865   0.04341   0.0108   0.0195   1.0000
  17.000   1.3909   0.05082   0.04563   0.0107   0.0191   1.0000
  17.250   1.3950   0.05312   0.04797   0.0106   0.0187   1.0000
  17.500   1.3971   0.05565   0.05056   0.0104   0.0183   1.0000
  17.750   1.4014   0.05797   0.05295   0.0102   0.0181   1.0000
  18.000   1.4056   0.06036   0.05540   0.0099   0.0178   1.0000
  18.250   1.4081   0.06299   0.05811   0.0095   0.0177   1.0000
  18.500   1.4124   0.06540   0.06058   0.0091   0.0171   1.0000
  18.750   1.4134   0.06828   0.06353   0.0085   0.0169   1.0000
  19.000   1.4147   0.07113   0.06645   0.0079   0.0166   1.0000
  19.250   1.4145   0.07427   0.06965   0.0071   0.0163   1.0000
<< Back to P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)

Polar data table (+)

Polar graphs


<< Back to P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)