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

NACA 63A010 AIRFOIL (n63010a-il)

NACA 63A010 AIRFOIL - NACA 63-010A airfoil


Airfoil n63010a-il
Details Dat file Parser  
(n63010a-il) NACA 63A010 AIRFOIL
NACA 63-010A airfoil
Max thickness 10% at 35% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 63A010 AIRFOIL
       26.       26.

  0.000000  0.000000
  0.005000  0.008160
  0.007500  0.009830
  0.012500  0.012500
  0.025000  0.017370
  0.050000  0.024120
  0.075000  0.029170
  0.100000  0.033240
  0.150000  0.039500
  0.200000  0.044000
  0.250000  0.047140
  0.300000  0.049130
  0.350000  0.049950
  0.400000  0.049680
  0.450000  0.048370
  0.500000  0.046130
  0.550000  0.043110
  0.600000  0.039430
  0.650000  0.035170
  0.700000  0.030440
  0.750000  0.025450
  0.800000  0.020400
  0.850000  0.015350
  0.900000  0.010300
  0.950000  0.005250
  1.000000  0.000210

  0.000000  0.000000
  0.005000 -0.008160
  0.007500 -0.009830
  0.012500 -0.012500
  0.025000 -0.017370
  0.050000 -0.024120
  0.075000 -0.029170
  0.100000 -0.033240
  0.150000 -0.039500
  0.200000 -0.044000
  0.250000 -0.047140
  0.300000 -0.049130
  0.350000 -0.049950
  0.400000 -0.049680
  0.450000 -0.048370
  0.500000 -0.046130
  0.550000 -0.043110
  0.600000 -0.039430
  0.650000 -0.035170
  0.700000 -0.030440
  0.750000 -0.025450
  0.800000 -0.020400
  0.850000 -0.015350
  0.900000 -0.010300
  0.950000 -0.005250
  1.000000 -0.000210
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RAE 102 AIRFOILPreviewDetails
HQ 0/10 AIRFOILPreviewDetails
FX 79-L-100PreviewDetails
NASA SC(2)-0010 AIRFOILPreviewDetails
RYAN BQM-34 FIREBEE WING AIRFOILPreviewDetails
NACA 0010PreviewDetails
RAE 101 AIRFOILPreviewDetails
NACA 0010-34PreviewDetails
NACA 0010-64PreviewDetails
NACA 64A-010 10.0%PreviewDetails

Polars for NACA 63A010 AIRFOIL (n63010a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n63010a-il50,000927.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63010a-il50,000526.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n63010a-il100,000937.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   n63010a-il100,000534.9 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n63010a-il200,000947.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n63010a-il200,000539.2 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n63010a-il500,000952.3 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63010a-il500,000551 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n63010a-il1,000,000959.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n63010a-il1,000,000564.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit