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N-13 (n13-il)

N-13 - N-13 airfoil


Airfoil n13-il
Details Dat file Parser  
(n13-il) N-13
N-13 airfoil
Max thickness 11.8% at 30% chord.
Max camber 0.1% at 95% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
N-13
1.0000     0.0000
0.9500     0.0102
0.9000     0.0160
0.8000     0.0302
0.7000     0.0400
0.6000     0.0486
0.5000     0.0552
0.4000     0.0580
0.3000     0.0584
0.2000     0.0546
0.1500     0.0504
0.1000     0.0438
0.0750     0.0390
0.0500     0.0328
0.0250     0.0238
0.0125     0.0166
0.0000     0.0000
0.0125     -0.0154
0.0250     -0.0228
0.0500     -0.0318
0.0750     -0.0392
0.1000     -0.0434
0.1500     -0.0504
0.2000     -0.0548
0.3000     -0.0596
0.4000     -0.0590
0.5000     -0.0552
0.6000     -0.0482
0.7000     -0.0388
0.8000     -0.0286
0.9000     -0.0160
0.9500     -0.0080
1.0000     0.0000
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Lednicer format dat file
Selig format dat file

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Polars for N-13 (n13-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n13-il50,000929 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n13-il50,000527.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n13-il100,000941.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n13-il100,000537.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n13-il200,000949.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   n13-il200,000545.8 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n13-il500,000960.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n13-il500,000560.8 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   n13-il1,000,000973.1 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   n13-il1,000,000571 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
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