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(1)-412 (naca651412-il)

NACA 65(1)-412 - NACA 65(1)-412 airfoil


Airfoil naca651412-il
Details Dat file Parser  
(naca651412-il) NACA 65(1)-412
NACA 65(1)-412 airfoil
Max thickness 12% at 39.9% chord.
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65(1)-412
1.00000     0.00000
0.95033     0.00986
0.90066     0.01979
0.85090     0.02974
0.80103     0.03935
0.75107     0.04847
0.70101     0.05686
0.65086     0.06440
0.60064     0.07085
0.55035     0.07602
0.50000     0.07963
0.44962     0.08139
0.39923     0.08139
0.34884     0.07971
0.29846     0.07658
0.24881     0.07193
0.19781     0.06562
0.14757     0.05741
0.09746     0.04672
0.07247     0.04010
0.04757     0.03227
0.02283     0.02234
0.01059     0.01588
0.00580     0.01236
0.00347     0.01010
0.00000     0.00000
0.00653     -0.00810
0.00920     -0.00956
0.01441     -0.01160
0.02717     -0.01490
0.05243     -0.01963
0.07753     -0.02314
0.10254     -0.02604
0.15243     -0.03049
0.20219     -0.03378
0.25189     -0.03613
0.30154     -0.03770
0.35116     -0.03851
0.40077     -0.03855
0.45038     -0.03759
0.50000     -0.03551
0.54965     -0.03222
0.59936     -0.02801
0.64914     -0.02320
0.69899     -0.01798
0.74893     -0.01267
0.79897     -0.00751
0.84910     -0.00282
0.89934     0.00089
0.94967     0.00278
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 548 AIRFOILPreviewDetails
LOCKHEED L-188 TIP AIRFOILPreviewDetails
NACA 65(1)-212 a=0.6PreviewDetails
NACA 63-412 AIRFOILPreviewDetails
HQ 2.0/12 AIRFOILPreviewDetails
HQ 2.5/12 AIRFOILPreviewDetails
LDS-2 AIRFOILPreviewDetails
RUTAN CANARD AIRFOILPreviewDetails
PSU-90-125WLPreviewDetails
HQ 1.5/12 AIRFOILPreviewDetails

Polars for NACA 65(1)-412 (naca651412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca651412-il50,000928.3 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651412-il50,000530.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651412-il100,000953 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651412-il100,000551.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651412-il200,000974.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651412-il200,000567.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651412-il500,000998.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651412-il500,000588.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651412-il1,000,0009116.3 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651412-il1,000,0005100.9 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit