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=200,000 Ncrit=9


Details Polar file
Airfoil: P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)
Reynolds number: 200,000
Max Cl/Cd: 62.43 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51droot-il-200000.txt
Download as CSV file: xf-p51droot-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6451   0.09650   0.09246  -0.0553   1.0000   0.0584
 -14.250  -0.6650   0.08862   0.08453  -0.0591   1.0000   0.0575
 -14.000  -0.7125   0.07795   0.07372  -0.0653   1.0000   0.0563
 -13.750  -0.7587   0.06937   0.06492  -0.0696   1.0000   0.0555
 -13.500  -0.7989   0.06257   0.05788  -0.0719   1.0000   0.0547
 -13.250  -0.8318   0.05724   0.05229  -0.0727   1.0000   0.0543
 -13.000  -0.8584   0.05298   0.04778  -0.0724   1.0000   0.0541
 -12.750  -0.8760   0.04985   0.04444  -0.0712   1.0000   0.0542
 -12.500  -0.8917   0.04725   0.04163  -0.0690   1.0000   0.0543
 -12.250  -0.9080   0.04546   0.03969  -0.0653   1.0000   0.0545
 -12.000  -0.9301   0.04450   0.03861  -0.0594   1.0000   0.0547
 -11.750  -0.9524   0.04362   0.03761  -0.0529   1.0000   0.0549
 -11.500  -0.9652   0.04234   0.03619  -0.0479   1.0000   0.0554
 -11.250  -0.9738   0.04096   0.03462  -0.0435   1.0000   0.0561
 -11.000  -0.9786   0.03949   0.03294  -0.0395   1.0000   0.0567
 -10.750  -0.9802   0.03804   0.03127  -0.0358   1.0000   0.0573
 -10.500  -0.9789   0.03665   0.02963  -0.0324   1.0000   0.0580
 -10.250  -0.9750   0.03544   0.02818  -0.0293   1.0000   0.0585
 -10.000  -0.9632   0.03331   0.02591  -0.0275   1.0000   0.0596
  -9.750  -0.9475   0.03195   0.02457  -0.0262   1.0000   0.0609
  -9.500  -0.9151   0.03075   0.02332  -0.0281   0.9969   0.0628
  -9.250  -0.8798   0.02949   0.02193  -0.0303   0.9936   0.0648
  -9.000  -0.8471   0.02832   0.02059  -0.0319   0.9896   0.0666
  -8.750  -0.8109   0.02698   0.01911  -0.0341   0.9857   0.0688
  -8.500  -0.7710   0.02572   0.01795  -0.0370   0.9827   0.0717
  -8.250  -0.7364   0.02484   0.01705  -0.0389   0.9782   0.0746
  -8.000  -0.7003   0.02401   0.01612  -0.0409   0.9734   0.0775
  -7.750  -0.6616   0.02278   0.01498  -0.0437   0.9701   0.0816
  -7.500  -0.6287   0.02203   0.01425  -0.0453   0.9648   0.0859
  -7.250  -0.5931   0.02120   0.01338  -0.0474   0.9595   0.0906
  -7.000  -0.5516   0.02021   0.01249  -0.0509   0.9559   0.0978
  -6.750  -0.5215   0.01941   0.01173  -0.0520   0.9491   0.1057
  -6.500  -0.4852   0.01858   0.01095  -0.0543   0.9435   0.1178
  -6.250  -0.4582   0.01773   0.01025  -0.0549   0.9362   0.1365
  -6.000  -0.4355   0.01673   0.00947  -0.0546   0.9279   0.1741
  -5.750  -0.4239   0.01564   0.00872  -0.0524   0.9166   0.2304
  -5.500  -0.4170   0.01422   0.00804  -0.0493   0.9056   0.3670
  -5.250  -0.4006   0.01370   0.00814  -0.0468   0.8960   0.4932
  -5.000  -0.3787   0.01380   0.00828  -0.0449   0.8839   0.5368
  -4.750  -0.3538   0.01390   0.00830  -0.0436   0.8732   0.5621
  -4.500  -0.3273   0.01398   0.00830  -0.0425   0.8634   0.5797
  -4.250  -0.3038   0.01402   0.00825  -0.0410   0.8491   0.5943
  -4.000  -0.2783   0.01412   0.00834  -0.0396   0.8345   0.6059
  -3.750  -0.2525   0.01419   0.00838  -0.0385   0.8191   0.6173
  -3.500  -0.2269   0.01426   0.00836  -0.0373   0.8029   0.6302
  -3.250  -0.1995   0.01442   0.00850  -0.0363   0.7870   0.6413
  -3.000  -0.1725   0.01451   0.00852  -0.0353   0.7718   0.6513
  -2.750  -0.1457   0.01455   0.00842  -0.0347   0.7574   0.6609
  -2.500  -0.1183   0.01449   0.00824  -0.0342   0.7446   0.6668
  -2.250  -0.0908   0.01453   0.00816  -0.0338   0.7328   0.6726
  -2.000  -0.0644   0.01452   0.00800  -0.0336   0.7215   0.6800
  -1.750  -0.0368   0.01455   0.00795  -0.0332   0.7129   0.6851
  -1.500  -0.0098   0.01466   0.00802  -0.0328   0.7042   0.6919
  -1.250   0.0174   0.01468   0.00787  -0.0328   0.6978   0.6990
  -1.000   0.0446   0.01469   0.00789  -0.0326   0.6908   0.7030
  -0.750   0.0722   0.01472   0.00787  -0.0325   0.6849   0.7077
  -0.500   0.1002   0.01477   0.00779  -0.0327   0.6802   0.7135
  -0.250   0.1272   0.01471   0.00773  -0.0328   0.6748   0.7174
   0.000   0.1548   0.01470   0.00771  -0.0328   0.6698   0.7204
   0.250   0.1830   0.01471   0.00768  -0.0330   0.6654   0.7235
   0.500   0.2114   0.01475   0.00766  -0.0333   0.6616   0.7268
   0.750   0.2390   0.01475   0.00767  -0.0337   0.6576   0.7304
   1.000   0.2670   0.01476   0.00764  -0.0341   0.6537   0.7335
   1.250   0.2950   0.01476   0.00765  -0.0342   0.6498   0.7358
   1.500   0.3236   0.01484   0.00769  -0.0344   0.6462   0.7386
   1.750   0.3508   0.01491   0.00781  -0.0346   0.6422   0.7419
   2.000   0.3780   0.01494   0.00788  -0.0347   0.6372   0.7450
   2.250   0.4062   0.01497   0.00786  -0.0349   0.6317   0.7482
   2.500   0.4350   0.01507   0.00789  -0.0353   0.6269   0.7512
   2.750   0.4609   0.01509   0.00803  -0.0351   0.6219   0.7541
   3.000   0.4879   0.01514   0.00814  -0.0350   0.6169   0.7574
   3.250   0.5164   0.01521   0.00818  -0.0352   0.6121   0.7607
   3.500   0.5439   0.01532   0.00832  -0.0353   0.6073   0.7643
   3.750   0.5703   0.01538   0.00844  -0.0353   0.6016   0.7680
   4.000   0.5979   0.01538   0.00847  -0.0353   0.5956   0.7711
   4.250   0.6256   0.01548   0.00860  -0.0352   0.5905   0.7748
   4.500   0.6506   0.01553   0.00877  -0.0348   0.5841   0.7792
   4.750   0.6783   0.01557   0.00883  -0.0349   0.5782   0.7838
   5.000   0.7057   0.01562   0.00891  -0.0348   0.5720   0.7879
   5.250   0.7301   0.01561   0.00903  -0.0342   0.5641   0.7920
   5.500   0.7585   0.01561   0.00904  -0.0342   0.5578   0.7969
   5.750   0.7823   0.01562   0.00919  -0.0335   0.5493   0.8027
   6.000   0.8090   0.01547   0.00902  -0.0330   0.5387   0.8080
   6.250   0.8303   0.01528   0.00895  -0.0316   0.5249   0.8146
   6.500   0.8523   0.01512   0.00888  -0.0305   0.5104   0.8222
   6.750   0.8729   0.01496   0.00884  -0.0289   0.4950   0.8292
   7.000   0.8927   0.01483   0.00878  -0.0274   0.4755   0.8388
   7.250   0.9090   0.01471   0.00876  -0.0251   0.4485   0.8486
   7.500   0.9202   0.01474   0.00873  -0.0220   0.3932   0.8618
   7.750   0.9125   0.01547   0.00898  -0.0161   0.3113   0.8819
   8.000   0.9085   0.01633   0.00964  -0.0111   0.2728   0.9128
   8.250   0.9317   0.01748   0.01070  -0.0120   0.2375   0.9673
   8.500   0.9444   0.01836   0.01142  -0.0110   0.2153   1.0000
   8.750   0.9538   0.01922   0.01215  -0.0090   0.1974   1.0000
   9.000   0.9628   0.02012   0.01295  -0.0070   0.1822   1.0000
   9.250   0.9712   0.02108   0.01383  -0.0050   0.1684   1.0000
   9.500   0.9790   0.02212   0.01481  -0.0030   0.1554   1.0000
   9.750   0.9857   0.02326   0.01590  -0.0009   0.1427   1.0000
  10.000   0.9913   0.02453   0.01710   0.0011   0.1307   1.0000
  10.250   0.9961   0.02590   0.01838   0.0031   0.1195   1.0000
  10.500   1.0045   0.02710   0.01957   0.0046   0.1090   1.0000
  10.750   1.0130   0.02836   0.02084   0.0060   0.1003   1.0000
  11.000   1.0185   0.02988   0.02225   0.0075   0.0937   1.0000
  11.250   1.0291   0.03110   0.02353   0.0086   0.0878   1.0000
  11.500   1.0356   0.03268   0.02501   0.0098   0.0833   1.0000
  11.750   1.0468   0.03397   0.02638   0.0108   0.0793   1.0000
  12.000   1.0570   0.03534   0.02776   0.0117   0.0758   1.0000
  12.250   1.0679   0.03682   0.02911   0.0127   0.0724   1.0000
  12.500   1.0801   0.03812   0.03054   0.0134   0.0700   1.0000
  12.750   1.0927   0.03944   0.03192   0.0141   0.0675   1.0000
  13.000   1.1053   0.04078   0.03325   0.0148   0.0652   1.0000
  13.250   1.1251   0.04196   0.03432   0.0155   0.0627   1.0000
  13.500   1.1364   0.04344   0.03595   0.0161   0.0611   1.0000
  13.750   1.1480   0.04496   0.03758   0.0167   0.0593   1.0000
  14.000   1.1613   0.04641   0.03909   0.0172   0.0577   1.0000
  14.250   1.1761   0.04779   0.04046   0.0176   0.0560   1.0000
  14.500   1.1983   0.04928   0.04193   0.0180   0.0541   1.0000
  14.750   1.2031   0.05134   0.04420   0.0186   0.0532   1.0000
  15.000   1.2076   0.05352   0.04656   0.0190   0.0520   1.0000
  15.250   1.2136   0.05569   0.04888   0.0193   0.0509   1.0000
  15.500   1.2185   0.05793   0.05123   0.0195   0.0498   1.0000
  15.750   1.2265   0.05996   0.05332   0.0196   0.0487   1.0000
  16.000   1.2496   0.06168   0.05496   0.0198   0.0471   1.0000
  16.250   1.2420   0.06509   0.05862   0.0198   0.0466   1.0000
  16.500   1.2305   0.06888   0.06267   0.0194   0.0462   1.0000
  16.750   1.2190   0.07299   0.06703   0.0187   0.0457   1.0000
  17.000   1.2049   0.07763   0.07192   0.0175   0.0452   1.0000
  17.250   1.1901   0.08260   0.07713   0.0160   0.0448   1.0000
  17.500   1.1716   0.08830   0.08306   0.0139   0.0445   1.0000
  17.750   1.1499   0.09476   0.08977   0.0112   0.0443   1.0000
  18.000   1.1232   0.10231   0.09757   0.0075   0.0442   1.0000
  18.250   1.0852   0.11242   0.10797   0.0019   0.0444   1.0000
  18.500   1.0280   0.12746   0.12334  -0.0072   0.0453   1.0000
  18.750   0.9290   0.15556   0.15174  -0.0248   0.0471   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)