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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 200,000
Max Cl/Cd: 54.8 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51dtip-il-200000.txt
Download as CSV file: xf-p51dtip-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3942   0.09390   0.09080  -0.0383   0.9087   0.0468
 -10.250  -0.3960   0.08926   0.08616  -0.0403   0.9050   0.0481
 -10.000  -0.4933   0.08632   0.08321  -0.0488   0.9364   0.0438
  -9.750  -0.4911   0.08153   0.07838  -0.0526   0.9252   0.0446
  -9.500  -0.4969   0.07649   0.07328  -0.0565   0.9155   0.0453
  -9.250  -0.5097   0.07168   0.06840  -0.0598   0.9068   0.0454
  -9.000  -0.5242   0.06802   0.06464  -0.0607   0.8992   0.0457
  -8.750  -0.5366   0.06494   0.06147  -0.0603   0.8925   0.0464
  -8.500  -0.5432   0.06172   0.05810  -0.0599   0.8872   0.0474
  -8.250  -0.5470   0.05843   0.05463  -0.0594   0.8824   0.0494
  -8.000  -0.5546   0.05770   0.05327  -0.0574   0.8766   0.0538
  -7.750  -0.5608   0.05243   0.04762  -0.0562   0.8729   0.0550
  -7.500  -0.5457   0.04778   0.04310  -0.0566   0.8705   0.0568
  -7.250  -0.5304   0.04516   0.04044  -0.0565   0.8674   0.0599
  -7.000  -0.5251   0.04380   0.03830  -0.0544   0.8637   0.0684
  -6.750  -0.5053   0.03985   0.03458  -0.0550   0.8613   0.0725
  -6.500  -0.4887   0.03198   0.02528  -0.0505   0.8586   0.0426
  -6.250  -0.4648   0.02947   0.02245  -0.0495   0.8563   0.0408
  -6.000  -0.4409   0.02777   0.02035  -0.0489   0.8535   0.0415
  -5.750  -0.4184   0.02419   0.01659  -0.0489   0.8510   0.0458
  -5.500  -0.3921   0.02271   0.01493  -0.0487   0.8488   0.0484
  -5.250  -0.3656   0.02168   0.01369  -0.0483   0.8468   0.0520
  -5.000  -0.3393   0.02079   0.01257  -0.0479   0.8450   0.0547
  -4.750  -0.3144   0.01926   0.01106  -0.0475   0.8434   0.0576
  -4.500  -0.2886   0.01864   0.01045  -0.0476   0.8414   0.0625
  -4.250  -0.2632   0.01801   0.00979  -0.0474   0.8393   0.0656
  -4.000  -0.2394   0.01737   0.00912  -0.0470   0.8370   0.0685
  -3.750  -0.2171   0.01673   0.00850  -0.0465   0.8348   0.0739
  -3.500  -0.1934   0.01632   0.00807  -0.0461   0.8329   0.0832
  -3.250  -0.1710   0.01573   0.00757  -0.0455   0.8313   0.1083
  -3.000  -0.1737   0.01346   0.00777  -0.0408   0.8295   0.6745
  -2.750  -0.1503   0.01422   0.00851  -0.0392   0.8278   0.7305
  -2.500  -0.1265   0.01488   0.00916  -0.0377   0.8261   0.7558
  -2.250  -0.1048   0.01563   0.00996  -0.0354   0.8243   0.7796
  -2.000  -0.0866   0.01645   0.01082  -0.0317   0.8225   0.8058
  -1.750  -0.0693   0.01708   0.01146  -0.0281   0.8206   0.8296
  -1.500  -0.0499   0.01747   0.01184  -0.0252   0.8193   0.8453
  -1.250  -0.0272   0.01766   0.01198  -0.0240   0.8181   0.8549
  -1.000  -0.0023   0.01771   0.01197  -0.0238   0.8170   0.8588
  -0.750   0.0236   0.01778   0.01198  -0.0239   0.8161   0.8612
  -0.500   0.0490   0.01790   0.01206  -0.0241   0.8151   0.8639
  -0.250   0.0722   0.01811   0.01226  -0.0246   0.8130   0.8665
   0.000   0.0958   0.01831   0.01244  -0.0251   0.8109   0.8686
   0.250   0.1203   0.01853   0.01265  -0.0258   0.8095   0.8700
   0.500   0.1444   0.01875   0.01287  -0.0262   0.8082   0.8711
   0.750   0.1682   0.01900   0.01312  -0.0265   0.8070   0.8723
   1.000   0.1925   0.01923   0.01336  -0.0267   0.8057   0.8737
   1.250   0.2174   0.01945   0.01360  -0.0269   0.8045   0.8754
   1.500   0.2418   0.01975   0.01393  -0.0272   0.8036   0.8772
   1.750   0.2689   0.01997   0.01418  -0.0277   0.8025   0.8787
   2.000   0.2859   0.02048   0.01473  -0.0272   0.7991   0.8810
   2.250   0.3029   0.02091   0.01520  -0.0266   0.7945   0.8834
   2.500   0.3287   0.02112   0.01546  -0.0268   0.7919   0.8851
   2.750   0.3599   0.02114   0.01557  -0.0274   0.7897   0.8866
   3.000   0.3795   0.02131   0.01582  -0.0263   0.7822   0.8892
   3.250   0.4310   0.01985   0.01440  -0.0274   0.7723   0.8893
   3.500   0.4668   0.01838   0.01299  -0.0262   0.7563   0.8905
   3.750   0.5005   0.01696   0.01160  -0.0249   0.7419   0.8920
   4.000   0.5320   0.01566   0.01034  -0.0236   0.7274   0.8938
   4.250   0.5619   0.01448   0.00923  -0.0225   0.7109   0.8961
   4.500   0.5911   0.01355   0.00838  -0.0217   0.6946   0.8984
   4.750   0.6176   0.01262   0.00757  -0.0204   0.6694   0.9009
   5.000   0.6368   0.01162   0.00605  -0.0171   0.4879   0.9044
   5.250   0.6230   0.01417   0.00703  -0.0114   0.2169   0.9116
   5.500   0.6227   0.01598   0.00803  -0.0077   0.0910   0.9177
   5.750   0.6384   0.01677   0.00882  -0.0061   0.0727   0.9238
   6.000   0.6544   0.01759   0.00964  -0.0046   0.0624   0.9303
   6.250   0.6713   0.01849   0.01052  -0.0034   0.0532   0.9384
   6.500   0.6934   0.01951   0.01164  -0.0029   0.0468   0.9472
   6.750   0.7198   0.02128   0.01336  -0.0033   0.0397   0.9562
   7.000   0.7550   0.02267   0.01490  -0.0047   0.0354   0.9661
   7.250   0.7926   0.02459   0.01696  -0.0066   0.0325   0.9787
   7.500   0.8287   0.02852   0.02105  -0.0085   0.0290   1.0000
   7.750   0.8533   0.03006   0.02290  -0.0082   0.0279   1.0000
   8.000   0.8775   0.03308   0.02630  -0.0080   0.0278   1.0000
   8.250   0.8966   0.03732   0.03094  -0.0073   0.0284   1.0000
  11.750   0.6990   0.10114   0.09814   0.0067   0.0522   1.0000
  12.000   0.6780   0.10781   0.10487   0.0029   0.0522   1.0000
  12.250   0.6586   0.11509   0.11220  -0.0021   0.0522   1.0000
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