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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 500,000
Max Cl/Cd: 74.06 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51dtip-il-500000.txt
Download as CSV file: xf-p51dtip-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5030   0.11408   0.11133  -0.0229   0.8318   0.0177
 -11.250  -0.5020   0.10960   0.10682  -0.0252   0.8291   0.0181
 -11.000  -0.5015   0.10489   0.10213  -0.0277   0.8263   0.0186
  -8.500  -0.6339   0.04626   0.04268  -0.0462   0.7973   0.0137
  -8.250  -0.6389   0.04113   0.03724  -0.0442   0.7948   0.0133
  -8.000  -0.6391   0.03574   0.03143  -0.0421   0.7925   0.0130
  -7.750  -0.6322   0.03078   0.02592  -0.0399   0.7905   0.0134
  -7.500  -0.6182   0.02730   0.02196  -0.0383   0.7886   0.0139
  -7.250  -0.5988   0.02505   0.01933  -0.0372   0.7868   0.0143
  -7.000  -0.5824   0.02059   0.01437  -0.0360   0.7849   0.0152
  -6.750  -0.5581   0.01994   0.01369  -0.0359   0.7828   0.0163
  -6.500  -0.5331   0.01922   0.01285  -0.0357   0.7807   0.0176
  -6.250  -0.5075   0.01850   0.01200  -0.0355   0.7787   0.0194
  -6.000  -0.4823   0.01766   0.01099  -0.0352   0.7770   0.0215
  -5.750  -0.4582   0.01655   0.00982  -0.0349   0.7754   0.0241
  -5.500  -0.4325   0.01606   0.00926  -0.0347   0.7739   0.0266
  -5.250  -0.4058   0.01573   0.00887  -0.0347   0.7723   0.0291
  -5.000  -0.3816   0.01467   0.00773  -0.0343   0.7706   0.0317
  -4.750  -0.3574   0.01391   0.00696  -0.0340   0.7688   0.0342
  -4.500  -0.3316   0.01352   0.00654  -0.0339   0.7671   0.0370
  -4.250  -0.3061   0.01308   0.00604  -0.0337   0.7656   0.0390
  -4.000  -0.2801   0.01272   0.00563  -0.0335   0.7641   0.0407
  -3.750  -0.2549   0.01226   0.00511  -0.0333   0.7627   0.0427
  -3.500  -0.2297   0.01180   0.00457  -0.0330   0.7613   0.0456
  -3.250  -0.2033   0.01154   0.00428  -0.0329   0.7599   0.0489
  -3.000  -0.1763   0.01131   0.00402  -0.0330   0.7585   0.0533
  -2.750  -0.1505   0.01083   0.00373  -0.0330   0.7570   0.0918
  -2.500  -0.1369   0.00853   0.00307  -0.0321   0.7553   0.5089
  -2.250  -0.1134   0.00832   0.00336  -0.0313   0.7538   0.6787
  -2.000  -0.0854   0.00847   0.00346  -0.0313   0.7525   0.7012
  -1.750  -0.0577   0.00862   0.00362  -0.0312   0.7513   0.7177
  -1.500  -0.0303   0.00882   0.00381  -0.0309   0.7501   0.7326
  -1.250  -0.0027   0.00901   0.00399  -0.0308   0.7490   0.7448
  -1.000   0.0243   0.00926   0.00426  -0.0304   0.7480   0.7583
  -0.750   0.0511   0.00946   0.00452  -0.0299   0.7470   0.7686
  -0.500   0.0795   0.00957   0.00456  -0.0301   0.7460   0.7726
  -0.250   0.1077   0.00958   0.00460  -0.0304   0.7448   0.7751
   0.000   0.1363   0.00961   0.00465  -0.0308   0.7436   0.7766
   0.250   0.1649   0.00965   0.00470  -0.0312   0.7424   0.7782
   0.500   0.1935   0.00971   0.00477  -0.0316   0.7412   0.7802
   0.750   0.2222   0.00976   0.00483  -0.0320   0.7400   0.7821
   1.000   0.2510   0.00978   0.00487  -0.0324   0.7385   0.7834
   1.250   0.2798   0.00979   0.00488  -0.0328   0.7368   0.7845
   1.500   0.3086   0.00980   0.00489  -0.0333   0.7353   0.7856
   1.750   0.3373   0.00979   0.00488  -0.0336   0.7336   0.7866
   2.000   0.3656   0.00972   0.00483  -0.0337   0.7302   0.7876
   2.250   0.3937   0.00940   0.00454  -0.0336   0.7222   0.7887
   2.500   0.4215   0.00890   0.00400  -0.0332   0.7092   0.7898
   2.750   0.4495   0.00861   0.00371  -0.0330   0.6993   0.7911
   3.000   0.4779   0.00850   0.00365  -0.0331   0.6934   0.7926
   3.250   0.5061   0.00838   0.00358  -0.0332   0.6860   0.7942
   3.500   0.5341   0.00819   0.00342  -0.0332   0.6736   0.7957
   3.750   0.5620   0.00806   0.00334  -0.0332   0.6580   0.7973
   4.000   0.5895   0.00796   0.00327  -0.0331   0.6310   0.7989
   4.250   0.6001   0.00938   0.00363  -0.0306   0.3858   0.8008
   4.500   0.6120   0.01088   0.00437  -0.0288   0.2097   0.8027
   4.750   0.6256   0.01214   0.00501  -0.0272   0.0801   0.8047
   5.000   0.6463   0.01277   0.00548  -0.0263   0.0498   0.8067
   5.250   0.6684   0.01326   0.00596  -0.0256   0.0420   0.8089
   5.500   0.6913   0.01367   0.00644  -0.0250   0.0378   0.8114
   5.750   0.7133   0.01415   0.00694  -0.0243   0.0326   0.8140
   6.000   0.7318   0.01487   0.00774  -0.0230   0.0280   0.8165
   6.250   0.7530   0.01534   0.00827  -0.0221   0.0240   0.8189
   6.500   0.7654   0.01667   0.00965  -0.0199   0.0201   0.8219
   6.750   0.7896   0.01685   0.00990  -0.0195   0.0182   0.8249
   7.000   0.8099   0.01747   0.01057  -0.0185   0.0164   0.8282
   7.250   0.8293   0.01810   0.01124  -0.0174   0.0151   0.8313
   7.500   0.8454   0.02004   0.01329  -0.0159   0.0138   0.8347
   7.750   0.8683   0.02108   0.01446  -0.0152   0.0132   0.8384
   8.000   0.8926   0.02246   0.01598  -0.0148   0.0127   0.8422
   8.250   0.9163   0.02389   0.01760  -0.0142   0.0121   0.8461
   8.500   0.9366   0.02457   0.01842  -0.0134   0.0112   0.8512
   8.750   0.9571   0.02574   0.01973  -0.0127   0.0107   0.8569
   9.000   0.9766   0.02749   0.02172  -0.0117   0.0104   0.8625
   9.250   0.9933   0.02909   0.02351  -0.0106   0.0100   0.8698
   9.500   1.0068   0.03167   0.02644  -0.0089   0.0099   0.8780
   9.750   1.0145   0.03420   0.02928  -0.0067   0.0097   0.8903
  16.000   0.7779   0.19020   0.18798  -0.0507   0.0137   1.0000
  16.250   0.7839   0.19468   0.19246  -0.0531   0.0136   1.0000
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