Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2424 (naca2424-il)

NACA 2424 - NACA 2424 airfoil


Airfoil naca2424-il
Details Dat file Parser  
(naca2424-il) NACA 2424
NACA 2424 airfoil
Max thickness 24% at 29.7% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2424
1.00000     0
0.95098     0.01930
0.90161     0.03502
0.80233     0.06352
0.70244     0.08824
0.60203     0.10903
0.50118     0.12532
0.40000     0.13606
0.29700     0.13874
0.24555     0.13593
0.19427     0.12959
0.14333     0.11888
0.09300     0.10215
0.06820     0.09052
0.04380     0.07552
0.02012     0.05449
0.00855     0.03892
0.00000     0.00000
0.01615     -0.03646
0.02988     -0.04965
0.05620     -0.06614
0.08180     -0.07692
0.10700     -0.08465
0.15667     -0.09450
0.20573     -0.09959
0.25445     -0.10155
0.30300     -0.10124
0.40000     -0.09606
0.49882     -0.08644
0.59797     -0.07347
0.69756     -0.05824
0.79767     -0.04130
0.89839     -0.02280
0.94902     -0.01292
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RAF 89 AIRFOILPreviewDetails
NACA 4424PreviewDetails
FX 83-W-227PreviewDetails
B-29 ROOT AIRFOILPreviewDetails
FX 84-W-218PreviewDetails
MH 150 23.89%PreviewDetails
GOE 776 AIRFOILPreviewDetails
NACA 2421PreviewDetails
EPPLER 858 AIRFOILPreviewDetails
AH 93-W-215PreviewDetails

Polars for NACA 2424 (naca2424-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2424-il50,00091.8 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2424-il50,000515.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2424-il100,000936.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2424-il100,000533.2 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2424-il200,000949 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2424-il200,000540.3 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2424-il500,000955 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2424-il500,000549.9 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2424-il1,000,000965.9 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2424-il1,000,000558.3 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit