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

NACA 63-215 AIRFOIL (n63215-il)

NACA 63-215 AIRFOIL - NACA 63(2)-215 airfoil


Airfoil n63215-il
Details Dat file Parser  
(n63215-il) NACA 63-215 AIRFOIL
NACA 63(2)-215 airfoil
Max thickness 15% at 34.9% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 63-215 AIRFOIL
      26.       26.

  0.000000  0.000000
  0.003990  0.012500
  0.006370  0.015280
  0.011200  0.019800
  0.023480  0.027920
  0.048290  0.039600
  0.073230  0.048470
  0.098230  0.055690
  0.148340  0.066820
  0.198520  0.074870
  0.248750  0.080490
  0.299000  0.083920
  0.349260  0.085300
  0.399520  0.084570
  0.449770  0.081940
  0.500000  0.077680
  0.550190  0.072030
  0.600350  0.065240
  0.650470  0.057510
  0.700530  0.049060
  0.750550  0.040140
  0.800510  0.031050
  0.850430  0.022130
  0.900300  0.013680
  0.950140  0.006160
  1.000000  0.000000

  0.000000  0.000000
  0.006010 -0.011500
  0.008630 -0.013880
  0.013800 -0.017660
  0.026520 -0.024200
  0.051710 -0.033280
  0.076770 -0.039990
  0.101770 -0.045350
  0.151660 -0.053360
  0.201480 -0.058950
  0.251250 -0.062590
  0.301000 -0.064480
  0.350740 -0.064700
  0.400480 -0.063150
  0.450230 -0.060040
  0.500000 -0.055620
  0.549810 -0.050130
  0.599650 -0.043820
  0.649530 -0.036910
  0.699470 -0.029620
  0.749450 -0.022240
  0.799490 -0.015130
  0.849570 -0.008670
  0.899700 -0.003340
  0.949860  0.000160
  1.000000  0.000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 64-215 AIRFOILPreviewDetails
NACA 64(2)-215PreviewDetails
NACA 65(2)-215PreviewDetails
NACA 63-415 AIRFOILPreviewDetails
NACA 64(2)-415PreviewDetails
HAWKER TEMPEST 37.5% SEMISPANPreviewDetails
NREL's S834 AirfoilPreviewDetails
NACA 65(2)-415PreviewDetails
E209 (13.72%)PreviewDetails
S8036 (16%)PreviewDetails

Polars for NACA 63-215 AIRFOIL (n63215-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n63215-il50,000929.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n63215-il50,000528.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n63215-il100,000948.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63215-il100,000546.5 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   n63215-il200,000965.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n63215-il200,000559.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n63215-il500,000985.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n63215-il500,000573.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n63215-il1,000,000998.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63215-il1,000,000580.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit