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NACA/LANGLEY SYMMETRICAL (n0011sc-il)

NACA/LANGLEY SYMMETRICAL - NASA/Langley 11% symmetrical supercritical airfoil


Airfoil n0011sc-il
Details Dat file Parser  
(n0011sc-il) NACA/LANGLEY SYMMETRICAL
NASA/Langley 11% symmetrical supercritical airfoil
Max thickness 11% at 40% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NACA/LANGLEY SYMMETRICAL, SUPERCRITICAL AIRFOIL
       37.       37.

 0.0000000 0.0000000
 0.0020000 0.0092250
 0.0065243 0.0157510
 0.0125000 0.0203230
 0.0250000 0.0262080
 0.0375000 0.0302420
 0.0500000 0.0333730
 0.0750000 0.0381170
 0.1000000 0.0416430
 0.1250000 0.0444000
 0.1500000 0.0466150
 0.1750000 0.0484210
 0.2000000 0.0499050
 0.2500000 0.0521250
 0.3000000 0.0535880
 0.3500000 0.0544670
 0.4000000 0.0547830
 0.4500000 0.0545710
 0.5000000 0.0537580
 0.5500000 0.0523760
 0.6000000 0.0504100
 0.6250000 0.0491980
 0.6500000 0.0478240
 0.6750000 0.0462810
 0.7000000 0.0445560
 0.7250000 0.0426350
 0.7500000 0.0404990
 0.7750000 0.0381270
 0.8000000 0.0354920
 0.8250000 0.0325640
 0.8500000 0.0293060
 0.8750000 0.0256760
 0.9000000 0.0216250
 0.9250000 0.0170990
 0.9500000 0.0120340
 0.9750000 0.0063610
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0020000 -.0092250
 0.0065243 -.0157510
 0.0125000 -.0203230
 0.0250000 -.0262080
 0.0375000 -.0302420
 0.0500000 -.0333730
 0.0750000 -.0381170
 0.1000000 -.0416430
 0.1250000 -.0444000
 0.1500000 -.0466150
 0.1750000 -.0484210
 0.2000000 -.0499050
 0.2500000 -.0521250
 0.3000000 -.0535880
 0.3500000 -.0544670
 0.4000000 -.0547830
 0.4500000 -.0545710
 0.5000000 -.0537580
 0.5500000 -.0523760
 0.6000000 -.0504100
 0.6250000 -.0491980
 0.6500000 -.0478240
 0.6750000 -.0462810
 0.7000000 -.0445560
 0.7250000 -.0426350
 0.7500000 -.0404990
 0.7750000 -.0381270
 0.8000000 -.0354920
 0.8250000 -.0325640
 0.8500000 -.0293060
 0.8750000 -.0256760
 0.9000000 -.0216250
 0.9250000 -.0170990
 0.9500000 -.0120340
 0.9750000 -.0063610
 1.0000000 0.0000000
Dat file parser warnings
  • Line 2 - Invalid characters : SUPERCRITICAL AIRFOIL
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Lednicer format dat file
Selig format dat file

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Polars for NACA/LANGLEY SYMMETRICAL (n0011sc-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n0011sc-il50,000922.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   n0011sc-il50,000522.3 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n0011sc-il100,000930.4 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   n0011sc-il100,000530.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n0011sc-il200,000941.5 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   n0011sc-il200,000539.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   n0011sc-il500,000949.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n0011sc-il500,000550.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n0011sc-il1,000,000959 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   n0011sc-il1,000,000562.6 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
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