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

NACA 4424 (naca4424-il)

NACA 4424 - NACA 4424 airfoil


Airfoil naca4424-il
Details Dat file Parser  
(naca4424-il) NACA 4424
NACA 4424 airfoil
Max thickness 24% at 29.4% chord.
Max camber 4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 4424
1.00000     0
0.95196     0.02240
0.90320     0.04099
0.80464     0.07447
0.70487     0.10312
0.60405     0.12674
0.50235     0.14474
0.40000     0.15606
0.29401     0.15738
0.24111     0.15287
0.18858     0.14416
0.13674     0.13045
0.08611     0.11012
0.06153     0.09651
0.03775     0.07942
0.01536     0.05624
0.00530     0.03964
0.00000     0.00000
0.01970     -0.03472
0.03464     -0.04656
0.06225     -0.06066
0.08847     -0.06931
0.11389     -0.07512
0.16326     -0.08169
0.21142     -0.08416
0.25889     -0.08411
0.30599     -0.08238
0.40000     -0.07606
0.49765     -0.06698
0.59595     -0.05562
0.69513     -0.04312
0.79536     -0.03003
0.89680     -0.01655
0.94804     -0.00964
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

MH 150 23.89%PreviewDetails
EPPLER 858 AIRFOILPreviewDetails
FX 83-W-227PreviewDetails
GOE 434 AIRFOILPreviewDetails
NACA 2424PreviewDetails
FX 84-W-218PreviewDetails
GOE 435 AIRFOILPreviewDetails
WORTMANN FX 77-W-258 AIRFOILPreviewDetails
GOE 522 AIRFOILPreviewDetails
RAF 89 AIRFOILPreviewDetails

Polars for NACA 4424 (naca4424-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca4424-il50,00092 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4424-il50,00058.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4424-il100,000930.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4424-il100,000533.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4424-il200,000953.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4424-il200,000545.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4424-il500,000964.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4424-il500,000555.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4424-il1,000,000973.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4424-il1,000,000564.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit