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NACA 64(1)-112 (naca641112-il)

NACA 64(1)-112 - NACA 64(1)-112 airfoil


Airfoil naca641112-il
Details Dat file Parser  
(naca641112-il) NACA 64(1)-112
NACA 64(1)-112 airfoil
Max thickness 12% at 40% chord.
Max camber 0.6% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 64(1)-112
1.00000     0.00000
0.95007     0.00446
0.90014     0.01044
0.85019     0.01718
0.80022     0.02427
0.75024     0.03143
0.70023     0.03836
0.65020     0.04489
0.60015     0.05084
0.55008     0.05604
0.50000     0.06032
0.44991     0.06346
0.39981     0.06517
0.34971     0.06493
0.29961     0.06330
0.24951     0.06024
0.19943     0.05571
0.14936     0.04956
0.09932     0.04128
0.07432     0.03605
0.04934     0.02967
0.02441     0.02127
0.01198     0.01543
0.00704     0.01213
0.00459     0.01002
0.00000     0.00000
0.00541     -0.00952
0.00796     -0.01143
0.01302     -0.01435
0.02559     -0.01941
0.05066     -0.02651
0.07568     -0.03181
0.10068     -0.03612
0.15064     -0.04284
0.20057     -0.04775
0.25049     -0.05128
0.30039     -0.05358
0.35029     -0.05463
0.40019     -0.05445
0.45009     -0.05250
0.50000     -0.04928
0.54992     -0.04508
0.59985     -0.04012
0.64980     -0.03459
0.69977     -0.02864
0.74976     -0.02247
0.79978     -0.01631
0.84981     -0.01046
0.89986     -0.00528
0.94993     -0.00130
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 64(1)-112 (naca641112-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca641112-il50,000929.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca641112-il50,000529.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca641112-il100,000944.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca641112-il100,000540 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca641112-il200,000954.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca641112-il200,000547.8 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca641112-il500,000968.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca641112-il500,000556 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca641112-il1,000,000976.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca641112-il1,000,000569.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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