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

NACA 65(3)-618 (naca653618-il)

NACA 65(3)-618 - NACA 65(3)-618 airfoil


Airfoil naca653618-il
Details Dat file Parser  
(naca653618-il) NACA 65(3)-618
NACA 65(3)-618 airfoil
Max thickness 18% at 39.8% chord.
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65(3)-618
1.00000	0.00000
0.95068	0.01433
0.90138	0.02863
0.85189	0.04306
0.80220	0.05719
0.75230	0.07075
0.70219	0.08338
0.65189	0.09482
0.60141	0.10479
0.55077	0.11293
0.50000	0.11877
0.44915	0.12186
0.39826	0.12210
0.34738	0.11972
0.29652	0.11504
0.24574	0.10803
0.19506	0.09848
0.14455	0.08602
0.09431	0.06978
0.06936	0.05971
0.04462	0.04776
0.02026	0.03268
0.00839	0.02293
0.00385	0.01776
0.00172	0.01446
0.00000	0.00000
0.00828	-0.01146
0.01115	-0.01356
0.01661	-0.01651
0.02974	-0.02152
0.05538	-0.0288
0.08064	-0.03427
0.10569	-0.03876
0.15545	-0.04564
0.20494	-0.05072
0.25426	-0.05433
0.30348	-0.05672
0.35262	-0.05792
0.40174	-0.05784
0.45085	-0.05616
0.50000	-0.05259
0.54923	-0.04723
0.59859	-0.04053
0.64811	-0.03302
0.69781	-0.02506
0.74770	-0.01705
0.79780	-0.00943
0.84811	-0.00268
0.89862	0.00239
0.94932	0.00463
1.00000	0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

HQ 3.5/18 AIRFOILPreviewDetails
NACA 63(3)-618PreviewDetails
NACA 64(3)-618PreviewDetails
FX S 03-182 AIRFOILPreviewDetails
RONCZ 1080 VOYAGER INNER AFT WINGPreviewDetails
RONCZ 1082 VOYAGER ROOT OUTER AFTPreviewDetails
WORTMANN FX 05-188 AIRFOILPreviewDetails
EPPLER 604 AIRFOILPreviewDetails
EPPLER 1098 AIRFOILPreviewDetails
EPPLER 1200 AIRFOILPreviewDetails

Polars for NACA 65(3)-618 (naca653618-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca653618-il50,000917.8 at α=12.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653618-il50,000515.3 at α=12.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653618-il100,000927.8 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653618-il100,000529 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653618-il200,000967.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653618-il200,000570.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653618-il500,0009110.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653618-il500,0005105.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653618-il1,000,0009138.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653618-il1,000,0005128.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit