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P-51D ROOT (BL17.5) AIRFOIL (p51droot-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)
Reynolds number: 100,000
Max Cl/Cd: 43.38 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51droot-il-100000-n5.txt
Download as CSV file: xf-p51droot-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6512   0.09419   0.08835  -0.0541   1.0000   0.0502
 -14.250  -0.7370   0.07694   0.07073  -0.0651   1.0000   0.0490
 -14.000  -0.7719   0.06980   0.06334  -0.0685   1.0000   0.0491
 -13.750  -0.7953   0.06465   0.05797  -0.0703   1.0000   0.0493
 -13.500  -0.8131   0.06045   0.05356  -0.0713   1.0000   0.0496
 -13.250  -0.8276   0.05682   0.04971  -0.0716   1.0000   0.0501
 -13.000  -0.8389   0.05364   0.04631  -0.0714   1.0000   0.0505
 -12.750  -0.8480   0.05080   0.04324  -0.0707   1.0000   0.0511
 -12.500  -0.8543   0.04831   0.04052  -0.0696   1.0000   0.0516
 -12.250  -0.8592   0.04610   0.03807  -0.0680   1.0000   0.0522
 -12.000  -0.8639   0.04423   0.03596  -0.0659   1.0000   0.0528
 -11.750  -0.8712   0.04278   0.03428  -0.0627   1.0000   0.0534
 -11.500  -0.8644   0.04144   0.03296  -0.0607   1.0000   0.0544
 -11.250  -0.8640   0.04050   0.03201  -0.0576   1.0000   0.0552
 -11.000  -0.8669   0.03964   0.03110  -0.0539   1.0000   0.0560
 -10.750  -0.8709   0.03884   0.03024  -0.0498   1.0000   0.0569
 -10.500  -0.8714   0.03793   0.02924  -0.0462   1.0000   0.0578
 -10.250  -0.8674   0.03692   0.02811  -0.0432   1.0000   0.0588
 -10.000  -0.8613   0.03589   0.02694  -0.0404   1.0000   0.0600
  -9.750  -0.8371   0.03456   0.02541  -0.0408   0.9966   0.0616
  -9.500  -0.8049   0.03318   0.02398  -0.0426   0.9919   0.0638
  -9.250  -0.7759   0.03205   0.02288  -0.0440   0.9869   0.0661
  -9.000  -0.7448   0.03097   0.02173  -0.0456   0.9827   0.0689
  -8.750  -0.7152   0.02995   0.02061  -0.0467   0.9781   0.0715
  -8.500  -0.6859   0.02892   0.01956  -0.0479   0.9732   0.0743
  -8.250  -0.6537   0.02794   0.01861  -0.0499   0.9690   0.0782
  -8.000  -0.6270   0.02712   0.01774  -0.0505   0.9631   0.0823
  -7.750  -0.5968   0.02617   0.01681  -0.0520   0.9580   0.0865
  -7.500  -0.5672   0.02535   0.01599  -0.0534   0.9527   0.0925
  -7.250  -0.5436   0.02460   0.01526  -0.0535   0.9452   0.0989
  -7.000  -0.5140   0.02385   0.01450  -0.0547   0.9396   0.1084
  -6.750  -0.4955   0.02317   0.01391  -0.0537   0.9305   0.1190
  -6.500  -0.4719   0.02247   0.01325  -0.0537   0.9232   0.1355
  -6.250  -0.4531   0.02178   0.01264  -0.0527   0.9141   0.1561
  -6.000  -0.4370   0.02106   0.01204  -0.0512   0.9041   0.1822
  -5.500  -0.4121   0.01909   0.01072  -0.0473   0.8829   0.2917
  -5.250  -0.4025   0.01824   0.01037  -0.0444   0.8706   0.3822
  -5.000  -0.3828   0.01814   0.01076  -0.0422   0.8606   0.4706
  -4.750  -0.3605   0.01816   0.01076  -0.0407   0.8489   0.5152
  -4.500  -0.3395   0.01823   0.01078  -0.0390   0.8351   0.5422
  -4.250  -0.3181   0.01836   0.01084  -0.0374   0.8206   0.5680
  -4.000  -0.2952   0.01866   0.01109  -0.0357   0.8057   0.5905
  -3.750  -0.2706   0.01887   0.01123  -0.0344   0.7911   0.6073
  -3.500  -0.2448   0.01886   0.01110  -0.0335   0.7774   0.6195
  -3.250  -0.2171   0.01881   0.01093  -0.0330   0.7651   0.6286
  -3.000  -0.1895   0.01869   0.01067  -0.0325   0.7530   0.6369
  -2.750  -0.1620   0.01867   0.01054  -0.0320   0.7411   0.6450
  -2.500  -0.1347   0.01859   0.01032  -0.0315   0.7309   0.6538
  -2.250  -0.1068   0.01860   0.01023  -0.0310   0.7213   0.6618
  -2.000  -0.0805   0.01848   0.00997  -0.0308   0.7119   0.6695
  -1.750  -0.0521   0.01844   0.00983  -0.0305   0.7038   0.6741
  -1.500  -0.0254   0.01838   0.00966  -0.0303   0.6955   0.6799
  -1.250   0.0013   0.01825   0.00938  -0.0303   0.6882   0.6857
  -1.000   0.0293   0.01821   0.00927  -0.0302   0.6817   0.6889
  -0.750   0.0564   0.01817   0.00919  -0.0301   0.6751   0.6925
  -0.500   0.0843   0.01811   0.00902  -0.0303   0.6699   0.6964
  -0.250   0.1120   0.01804   0.00885  -0.0306   0.6650   0.7004
   0.000   0.1389   0.01802   0.00880  -0.0306   0.6598   0.7037
   0.250   0.1667   0.01802   0.00879  -0.0307   0.6552   0.7065
   0.500   0.1951   0.01802   0.00873  -0.0309   0.6513   0.7094
   0.750   0.2224   0.01805   0.00873  -0.0310   0.6470   0.7128
   1.000   0.2492   0.01808   0.00875  -0.0312   0.6424   0.7167
   1.250   0.2767   0.01812   0.00877  -0.0314   0.6384   0.7200
   1.500   0.3049   0.01817   0.00882  -0.0315   0.6351   0.7225
   1.750   0.3336   0.01825   0.00889  -0.0318   0.6324   0.7254
   2.000   0.3596   0.01837   0.00908  -0.0318   0.6289   0.7290
   2.250   0.3859   0.01849   0.00924  -0.0318   0.6253   0.7329
   2.750   0.4410   0.01868   0.00946  -0.0320   0.6169   0.7394
   3.000   0.4678   0.01881   0.00964  -0.0320   0.6126   0.7425
   3.250   0.4924   0.01896   0.00989  -0.0316   0.6071   0.7463
   3.500   0.5194   0.01904   0.00999  -0.0316   0.6011   0.7507
   3.750   0.5469   0.01912   0.01008  -0.0316   0.5950   0.7549
   4.000   0.5704   0.01925   0.01034  -0.0309   0.5875   0.7586
   4.250   0.5983   0.01928   0.01039  -0.0308   0.5810   0.7626
   4.500   0.6215   0.01941   0.01062  -0.0302   0.5731   0.7672
   4.750   0.6477   0.01946   0.01072  -0.0299   0.5653   0.7722
   5.000   0.6718   0.01954   0.01091  -0.0292   0.5574   0.7768
   5.250   0.6959   0.01961   0.01108  -0.0285   0.5489   0.7826
   5.500   0.7209   0.01968   0.01123  -0.0280   0.5408   0.7891
   5.750   0.7434   0.01973   0.01143  -0.0270   0.5313   0.7947
   6.000   0.7663   0.01981   0.01163  -0.0261   0.5222   0.8017
   6.250   0.7893   0.01984   0.01179  -0.0252   0.5123   0.8091
   6.500   0.8088   0.01993   0.01207  -0.0238   0.5008   0.8180
   6.750   0.8285   0.01995   0.01223  -0.0223   0.4871   0.8285
   7.000   0.8449   0.01996   0.01239  -0.0203   0.4676   0.8416
   7.250   0.8587   0.01997   0.01251  -0.0178   0.4411   0.8574
   7.500   0.8697   0.02005   0.01265  -0.0149   0.3950   0.8772
   7.750   0.8744   0.02044   0.01258  -0.0112   0.3201   0.9055
   8.000   0.8833   0.02165   0.01344  -0.0097   0.2745   0.9556
   8.250   0.8868   0.02276   0.01436  -0.0072   0.2511   1.0000
   8.500   0.8923   0.02380   0.01532  -0.0049   0.2302   1.0000
   8.750   0.8988   0.02486   0.01630  -0.0028   0.2112   1.0000
   9.000   0.9053   0.02597   0.01734  -0.0008   0.1943   1.0000
   9.250   0.9119   0.02714   0.01842   0.0010   0.1801   1.0000
   9.500   0.9183   0.02837   0.01958   0.0027   0.1676   1.0000
   9.750   0.9241   0.02970   0.02080   0.0043   0.1570   1.0000
  10.000   0.9331   0.03091   0.02203   0.0057   0.1460   1.0000
  10.250   0.9415   0.03221   0.02331   0.0069   0.1363   1.0000
  10.500   0.9487   0.03363   0.02469   0.0081   0.1272   1.0000
  10.750   0.9592   0.03489   0.02600   0.0090   0.1175   1.0000
  11.000   0.9677   0.03634   0.02743   0.0100   0.1096   1.0000
  11.250   0.9763   0.03782   0.02893   0.0108   0.1017   1.0000
  11.500   0.9856   0.03929   0.03043   0.0116   0.0952   1.0000
  11.750   0.9933   0.04093   0.03205   0.0122   0.0895   1.0000
  12.000   1.0021   0.04252   0.03366   0.0129   0.0845   1.0000
  12.250   1.0105   0.04419   0.03535   0.0134   0.0800   1.0000
  12.500   1.0170   0.04603   0.03716   0.0140   0.0770   1.0000
  12.750   1.0278   0.04759   0.03882   0.0145   0.0736   1.0000
  13.000   1.0368   0.04931   0.04060   0.0149   0.0707   1.0000
  13.250   1.0438   0.05122   0.04251   0.0152   0.0681   1.0000
  13.500   1.0522   0.05306   0.04436   0.0156   0.0659   1.0000
  13.750   1.0618   0.05489   0.04633   0.0159   0.0635   1.0000
  14.000   1.0707   0.05678   0.04832   0.0162   0.0616   1.0000
  14.250   1.0789   0.05876   0.05035   0.0163   0.0599   1.0000
  14.500   1.0869   0.06075   0.05235   0.0164   0.0584   1.0000
  14.750   1.0958   0.06277   0.05441   0.0166   0.0570   1.0000
  15.000   1.1006   0.06531   0.05717   0.0165   0.0554   1.0000
  15.250   1.1047   0.06794   0.05997   0.0163   0.0540   1.0000
  15.500   1.1083   0.07063   0.06281   0.0160   0.0527   1.0000
  15.750   1.1120   0.07336   0.06564   0.0156   0.0516   1.0000
  16.000   1.1160   0.07605   0.06840   0.0151   0.0506   1.0000
  16.250   1.1228   0.07843   0.07078   0.0148   0.0496   1.0000
  16.500   1.1208   0.08207   0.07459   0.0140   0.0488   1.0000
  16.750   1.1105   0.08687   0.07968   0.0123   0.0480   1.0000
  17.000   1.0988   0.09207   0.08513   0.0103   0.0473   1.0000
  17.250   1.0848   0.09782   0.09113   0.0078   0.0467   1.0000
  17.500   1.0679   0.10428   0.09783   0.0046   0.0462   1.0000
  17.750   1.0457   0.11202   0.10582   0.0005   0.0458   1.0000
  18.000   1.0118   0.12267   0.11675  -0.0058   0.0457   1.0000
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