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P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)

P-51D ROOT (BL17.5) AIRFOIL - P-51D root (BL17.5) airfoil


Airfoil p51droot-il
Details Dat file Parser  
(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL
P-51D root (BL17.5) airfoil
Max thickness 16.5% at 38.9% chord.
Max camber 1.3% at 68.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
P-51D ROOT (BL17.5) AIRFOIL
      21.0      21.0

 0.0000000 0.0000000
 0.0055850 0.0152580
 0.0222140 0.0303390
 0.0495160 0.0447680
 0.0868810 0.0584290
 0.1334740 0.0697510
 0.1882550 0.0798820
 0.2500000 0.0873110
 0.3173300 0.0932430
 0.3887400 0.0947010
 0.4626350 0.0900310
 0.5373650 0.0814770
 0.6112610 0.0716860
 0.6826710 0.0615620
 0.7500000 0.0507660
 0.8117450 0.0381450
 0.8665260 0.0245870
 0.9131190 0.0137010
 0.9504850 0.0067200
 0.9777860 0.0027970
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0055850 -.0133190
 0.0222140 -.0264060
 0.0495160 -.0369920
 0.0868810 -.0467250
 0.1334740 -.0547400
 0.1882550 -.0614090
 0.2500000 -.0672010
 0.3173300 -.0700780
 0.3887400 -.0704490
 0.4626350 -.0673520
 0.5373650 -.0594540
 0.6112610 -.0479390
 0.6826710 -.0362640
 0.7500000 -.0265480
 0.8117450 -.0181180
 0.8665260 -.0105930
 0.9131190 -.0053840
 0.9504850 -.0025090
 0.9777860 -.0010200
 1.0000000 0.0000000
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Polars for P-51D ROOT (BL17.5) AIRFOIL (p51droot-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   p51droot-il50,000928 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   p51droot-il50,000523.9 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   p51droot-il100,000946.2 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   p51droot-il100,000543.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   p51droot-il200,000962.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   p51droot-il200,000557.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   p51droot-il500,000981.3 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   p51droot-il500,000571.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   p51droot-il1,000,000992.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   p51droot-il1,000,000579.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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