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P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il)
Reynolds number: 100,000
Max Cl/Cd: 40.82 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-p51dtip-il-100000.txt
Download as CSV file: xf-p51dtip-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5151   0.09505   0.09086  -0.0428   1.0000   0.1081
  -9.500  -0.4907   0.09193   0.08773  -0.0385   1.0000   0.1157
  -9.250  -0.5015   0.08727   0.08315  -0.0439   1.0000   0.1202
  -9.000  -0.5269   0.08321   0.07919  -0.0484   1.0000   0.1212
  -8.750  -0.5541   0.08238   0.07845  -0.0442   1.0000   0.1207
  -8.500  -0.5789   0.08097   0.07707  -0.0411   0.9980   0.1201
  -8.250  -0.6100   0.07701   0.07267  -0.0497   0.9837   0.1226
  -8.000  -0.5842   0.07190   0.06772  -0.0502   0.9818   0.1354
  -7.750  -0.4923   0.05595   0.05204  -0.0553   0.9711   0.1624
  -7.500  -0.5682   0.06364   0.05930  -0.0529   0.9718   0.1548
  -7.250  -0.5571   0.06008   0.05564  -0.0542   0.9681   0.1698
  -6.000  -0.5005   0.03789   0.03023  -0.0503   0.9458   0.0798
  -5.750  -0.4770   0.03430   0.02631  -0.0500   0.9438   0.0767
  -5.500  -0.4497   0.03176   0.02328  -0.0499   0.9420   0.0766
  -5.250  -0.4327   0.03068   0.02175  -0.0479   0.9396   0.0800
  -5.000  -0.4169   0.02944   0.02017  -0.0456   0.9370   0.0808
  -4.750  -0.3936   0.02736   0.01803  -0.0449   0.9349   0.0838
  -4.500  -0.3700   0.02637   0.01696  -0.0445   0.9328   0.0904
  -4.250  -0.3444   0.02545   0.01588  -0.0439   0.9312   0.0938
  -4.000  -0.3207   0.02437   0.01486  -0.0433   0.9300   0.0979
  -3.750  -0.2987   0.02378   0.01430  -0.0426   0.9287   0.1071
  -3.500  -0.2789   0.02312   0.01374  -0.0416   0.9276   0.1171
  -3.250  -0.2689   0.02273   0.01335  -0.0387   0.9261   0.1281
  -3.000  -0.2600   0.02212   0.01296  -0.0357   0.9244   0.1602
  -2.750  -0.2752   0.02030   0.01371  -0.0276   0.9234   0.6795
  -2.500  -0.0461   0.02541   0.01843  -0.0443   0.9294   0.9375
  -2.250   0.0129   0.02510   0.01791  -0.0511   0.9293   0.9493
  -2.000   0.0523   0.02497   0.01761  -0.0544   0.9284   0.9571
  -1.750   0.0945   0.02482   0.01733  -0.0584   0.9275   0.9634
  -1.500   0.0827   0.02527   0.01777  -0.0524   0.9247   0.9695
  -1.250   0.0988   0.02537   0.01782  -0.0517   0.9235   0.9735
  -1.000   0.1053   0.02562   0.01802  -0.0493   0.9224   0.9768
  -0.750   0.1077   0.02588   0.01825  -0.0460   0.9208   0.9786
  -0.500   0.1102   0.02616   0.01850  -0.0428   0.9199   0.9806
  -0.250   0.1139   0.02642   0.01875  -0.0399   0.9199   0.9828
   0.000   0.1232   0.02663   0.01894  -0.0381   0.9199   0.9845
   0.250   0.1373   0.02684   0.01914  -0.0371   0.9195   0.9868
   0.500   0.1486   0.02710   0.01940  -0.0357   0.9202   0.9896
   0.750   0.1575   0.02739   0.01969  -0.0339   0.9215   0.9923
   1.000   0.1713   0.02767   0.01998  -0.0330   0.9218   0.9949
   1.250   0.1901   0.02800   0.02032  -0.0331   0.9229   0.9983
   1.500   0.1999   0.02836   0.02070  -0.0316   0.9248   1.0000
   1.750   0.2006   0.02868   0.02104  -0.0283   0.9264   1.0000
   2.000   0.1589   0.02836   0.02072  -0.0177   0.9349   1.0000
   2.250   0.1519   0.02840   0.02077  -0.0131   0.9381   1.0000
   2.500   0.1492   0.02832   0.02073  -0.0091   0.9368   1.0000
   2.750   0.1809   0.02886   0.02131  -0.0109   0.9243   1.0000
   3.000   0.1827   0.02888   0.02134  -0.0077   0.9215   1.0000
   3.250   0.1925   0.02918   0.02168  -0.0062   0.9212   1.0000
   3.500   0.2269   0.02996   0.02252  -0.0084   0.9102   1.0000
   3.750   0.2641   0.03073   0.02342  -0.0110   0.8973   1.0000
   4.000   0.2981   0.03120   0.02400  -0.0126   0.8793   1.0000
   4.250   0.3650   0.03157   0.02458  -0.0180   0.8465   1.0000
   4.500   0.4150   0.03161   0.02486  -0.0207   0.8215   1.0000
   4.750   0.7289   0.01796   0.01233  -0.0425   0.6733   1.0000
   5.000   0.7099   0.01739   0.01003  -0.0311   0.3132   1.0000
   5.250   0.6867   0.01940   0.01100  -0.0237   0.1747   1.0000
   5.500   0.6761   0.02049   0.01166  -0.0177   0.1329   1.0000
   5.750   0.6703   0.02118   0.01220  -0.0124   0.1157   1.0000
   6.000   0.6730   0.02210   0.01299  -0.0086   0.1037   1.0000
   6.250   0.6888   0.02329   0.01407  -0.0070   0.0895   1.0000
   6.500   0.7158   0.02510   0.01568  -0.0069   0.0776   1.0000
   6.750   0.7426   0.02637   0.01708  -0.0067   0.0678   1.0000
   7.000   0.7799   0.02913   0.01990  -0.0076   0.0624   1.0000
   7.250   0.8078   0.03097   0.02197  -0.0076   0.0565   1.0000
   7.500   0.8371   0.03380   0.02499  -0.0079   0.0541   1.0000
   7.750   0.8636   0.03713   0.02872  -0.0074   0.0541   1.0000
   8.000   0.8821   0.04126   0.03368  -0.0054   0.0576   1.0000
   8.250   0.8967   0.04553   0.03846  -0.0038   0.0599   1.0000
   8.500   0.9080   0.04982   0.04312  -0.0023   0.0618   1.0000
   8.750   0.8579   0.04536   0.03981   0.0048   0.0744   1.0000
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