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 TIP (BL215) AIRFOIL (p51dtip-il)

P-51D TIP (BL215) AIRFOIL - P-51D tip (BL215) airfoil


Airfoil p51dtip-il
Details Dat file Parser  
(p51dtip-il) P-51D TIP (BL215) AIRFOIL
P-51D tip (BL215) airfoil
Max thickness 11.4% at 46.3% chord.
Max camber 1.3% at 46.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
P-51D TIP (BL215) AIRFOIL
      21.0      21.0

 0.0000000 0.0000000
 0.0055846 0.0080857
 0.0222136 0.0171943
 0.0495156 0.0265966
 0.0868806 0.0357669
 0.1334741 0.0443234
 0.1882551 0.0519490
 0.2500000 0.0586048
 0.3173295 0.0639389
 0.3887396 0.0675523
 0.4626350 0.0700939
 0.5373651 0.0689003
 0.6112605 0.0620020
 0.6826705 0.0504744
 0.7500001 0.0370719
 0.8117449 0.0250994
 0.8665259 0.0161636
 0.9131194 0.0094824
 0.9504845 0.0047928
 0.9777864 0.0020193
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0055846 -.0072395
 0.0222136 -.0141771
 0.0495156 -.0199017
 0.0868806 -.0253040
 0.1334741 -.0305286
 0.1882551 -.0350210
 0.2500000 -.0385206
 0.3173295 -.0414433
 0.3887396 -.0429331
 0.4626350 -.0440883
 0.5373651 -.0435437
 0.6112605 -.0389807
 0.6826705 -.0301552
 0.7500001 -.0205715
 0.8117449 -.0123279
 0.8665259 -.0063297
 0.9131194 -.0029648
 0.9504845 -.0014429
 0.9777864 -.0006126
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 66PreviewDetails
NACA 66(1)-212PreviewDetails
MH 26 10.99%PreviewDetails
MH 27 11.99%PreviewDetails
LOCKHEED C-141 BL426.57 AIRFOILPreviewDetails
GOE 780 AIRFOILPreviewDetails
LOCKHEED C-141 BL610.61 AIRFOILPreviewDetails
NACA 65(1)-212 a=0.6PreviewDetails
NACA 64(1)-212PreviewDetails
NACA 65(1)-212PreviewDetails

Polars for P-51D TIP (BL215) AIRFOIL (p51dtip-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   p51dtip-il50,000922.6 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   p51dtip-il50,000523.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   p51dtip-il100,000940.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   p51dtip-il100,000535.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   p51dtip-il200,000954.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   p51dtip-il200,000549.4 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   p51dtip-il500,000974.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   p51dtip-il500,000563.7 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   p51dtip-il1,000,000989.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   p51dtip-il1,000,000568.4 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit