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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 200,000
Max Cl/Cd: 49.38 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51dtip-il-200000-n5.txt
Download as CSV file: xf-p51dtip-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5279   0.09016   0.08643  -0.0347   0.8345   0.0124
 -10.250  -0.5350   0.08407   0.08035  -0.0385   0.8311   0.0122
 -10.000  -0.5478   0.07636   0.07265  -0.0445   0.8271   0.0121
  -9.750  -0.5645   0.06982   0.06605  -0.0488   0.8231   0.0119
  -9.500  -0.5842   0.06451   0.06062  -0.0508   0.8193   0.0118
  -9.250  -0.6025   0.06028   0.05627  -0.0509   0.8154   0.0117
  -9.000  -0.6191   0.05609   0.05191  -0.0497   0.8117   0.0117
  -8.750  -0.6289   0.05145   0.04700  -0.0485   0.8086   0.0117
  -8.500  -0.6348   0.04650   0.04171  -0.0469   0.8060   0.0118
  -8.250  -0.6367   0.04124   0.03601  -0.0451   0.8034   0.0120
  -8.000  -0.6333   0.03600   0.03023  -0.0432   0.8005   0.0123
  -7.750  -0.6238   0.03139   0.02499  -0.0414   0.7977   0.0131
  -7.500  -0.6064   0.02844   0.02152  -0.0403   0.7953   0.0142
  -7.250  -0.5864   0.02630   0.01899  -0.0395   0.7931   0.0154
  -7.000  -0.5653   0.02504   0.01756  -0.0391   0.7913   0.0169
  -6.750  -0.5418   0.02379   0.01610  -0.0387   0.7893   0.0185
  -6.500  -0.5173   0.02237   0.01443  -0.0383   0.7871   0.0211
  -6.250  -0.4919   0.02141   0.01318  -0.0380   0.7850   0.0242
  -6.000  -0.4674   0.02054   0.01220  -0.0378   0.7830   0.0269
  -5.750  -0.4427   0.01981   0.01139  -0.0376   0.7811   0.0294
  -5.500  -0.4171   0.01939   0.01078  -0.0374   0.7794   0.0329
  -5.250  -0.3937   0.01831   0.00968  -0.0369   0.7778   0.0352
  -5.000  -0.3692   0.01768   0.00896  -0.0366   0.7759   0.0374
  -4.750  -0.3444   0.01712   0.00834  -0.0364   0.7737   0.0394
  -4.500  -0.3194   0.01665   0.00778  -0.0362   0.7718   0.0410
  -4.250  -0.2949   0.01614   0.00722  -0.0359   0.7700   0.0426
  -4.000  -0.2706   0.01566   0.00672  -0.0357   0.7683   0.0462
  -3.750  -0.2452   0.01531   0.00632  -0.0355   0.7668   0.0489
  -3.500  -0.2196   0.01499   0.00587  -0.0354   0.7654   0.0510
  -3.250  -0.1937   0.01470   0.00550  -0.0352   0.7641   0.0545
  -3.000  -0.1681   0.01437   0.00518  -0.0351   0.7629   0.0657
  -2.750  -0.1445   0.01370   0.00487  -0.0350   0.7609   0.1395
  -2.500  -0.1272   0.01227   0.00447  -0.0344   0.7588   0.3930
  -2.250  -0.1107   0.01169   0.00494  -0.0321   0.7569   0.6709
  -2.000  -0.0845   0.01194   0.00518  -0.0315   0.7554   0.7080
  -1.750  -0.0590   0.01226   0.00550  -0.0306   0.7540   0.7350
  -1.500  -0.0335   0.01254   0.00579  -0.0297   0.7528   0.7520
  -1.250  -0.0078   0.01278   0.00600  -0.0290   0.7516   0.7658
  -1.000   0.0189   0.01293   0.00609  -0.0287   0.7506   0.7760
  -0.750   0.0463   0.01297   0.00610  -0.0286   0.7497   0.7788
  -0.500   0.0744   0.01300   0.00610  -0.0290   0.7484   0.7806
  -0.250   0.1026   0.01304   0.00613  -0.0294   0.7467   0.7819
   0.000   0.1308   0.01308   0.00616  -0.0299   0.7450   0.7833
   0.250   0.1590   0.01312   0.00620  -0.0303   0.7434   0.7848
   0.500   0.1873   0.01317   0.00624  -0.0308   0.7421   0.7863
   0.750   0.2156   0.01323   0.00630  -0.0312   0.7409   0.7876
   1.000   0.2440   0.01329   0.00638  -0.0317   0.7398   0.7890
   1.250   0.2723   0.01337   0.00647  -0.0322   0.7388   0.7903
   1.500   0.3003   0.01344   0.00659  -0.0325   0.7378   0.7914
   1.750   0.3283   0.01353   0.00673  -0.0328   0.7370   0.7925
   2.000   0.3563   0.01361   0.00687  -0.0330   0.7360   0.7940
   2.250   0.3838   0.01372   0.00707  -0.0333   0.7337   0.7956
   2.500   0.4108   0.01384   0.00729  -0.0336   0.7303   0.7974
   2.750   0.4386   0.01371   0.00724  -0.0335   0.7253   0.7991
   3.000   0.4659   0.01322   0.00677  -0.0328   0.7133   0.8008
   3.250   0.4936   0.01245   0.00597  -0.0319   0.6951   0.8026
   3.500   0.5203   0.01205   0.00563  -0.0314   0.6753   0.8044
   3.750   0.5470   0.01181   0.00552  -0.0310   0.6560   0.8059
   4.000   0.5733   0.01161   0.00539  -0.0305   0.6260   0.8076
   4.250   0.5852   0.01218   0.00494  -0.0273   0.4060   0.8099
   4.500   0.5966   0.01347   0.00566  -0.0253   0.2771   0.8127
   4.750   0.6113   0.01450   0.00627  -0.0238   0.1842   0.8158
   5.000   0.6278   0.01539   0.00684  -0.0226   0.1143   0.8187
   5.250   0.6450   0.01615   0.00742  -0.0213   0.0724   0.8211
   5.500   0.6644   0.01676   0.00799  -0.0202   0.0561   0.8238
   5.750   0.6839   0.01737   0.00867  -0.0192   0.0481   0.8269
   6.000   0.7044   0.01789   0.00927  -0.0184   0.0425   0.8303
   6.250   0.7232   0.01851   0.00992  -0.0173   0.0363   0.8335
   6.500   0.7400   0.01925   0.01069  -0.0160   0.0313   0.8369
   6.750   0.7597   0.01978   0.01132  -0.0150   0.0256   0.8409
   7.000   0.7760   0.02067   0.01227  -0.0136   0.0223   0.8456
   7.250   0.7926   0.02152   0.01328  -0.0120   0.0194   0.8500
   7.500   0.8099   0.02240   0.01424  -0.0106   0.0168   0.8554
   7.750   0.8269   0.02345   0.01535  -0.0094   0.0149   0.8611
   8.000   0.8468   0.02454   0.01657  -0.0084   0.0135   0.8670
   8.250   0.8703   0.02602   0.01824  -0.0080   0.0126   0.8732
   8.500   0.8956   0.02784   0.02031  -0.0077   0.0117   0.8795
   8.750   0.9197   0.03000   0.02288  -0.0073   0.0111   0.8874
   9.000   0.9405   0.03250   0.02579  -0.0065   0.0106   0.8978
   9.500   0.9757   0.03702   0.03110  -0.0053   0.0092   1.0000
   9.750   0.9855   0.03876   0.03306  -0.0039   0.0086   1.0000
  10.000   0.9898   0.04083   0.03535  -0.0018   0.0082   1.0000
  10.250   0.9887   0.04345   0.03825   0.0006   0.0080   1.0000
  10.500   0.9829   0.04638   0.04144   0.0031   0.0078   1.0000
  10.750   0.9733   0.04990   0.04526   0.0053   0.0078   1.0000
  11.000   0.9598   0.05371   0.04933   0.0071   0.0078   1.0000
  11.250   0.9436   0.05796   0.05384   0.0084   0.0078   1.0000
  11.500   0.9252   0.06253   0.05863   0.0090   0.0078   1.0000
  11.750   0.9049   0.06765   0.06395   0.0086   0.0078   1.0000
  12.000   0.8764   0.07498   0.07151   0.0069   0.0080   1.0000
  12.250   0.8465   0.08362   0.08035   0.0031   0.0081   1.0000
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