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STRAND AIRFOIL (strand-il)

STRAND AIRFOIL - Strand high lift airfoil


Airfoil strand-il
Details Dat file Parser  
(strand-il) STRAND AIRFOIL
Strand high lift airfoil
Max thickness 15.4% at 26.1% chord.
Max camber 4.1% at 32.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 
 STRAND AIRFOIL
20.        20.

 0.0000    0.0000
 0.0044    0.0133
 0.0114    0.0232
 0.0198    0.0320
 0.0488    0.0541
 0.1030    0.0815
 0.1607    0.1005
 0.2003    0.1093
 0.2607    0.1167
 0.3214    0.1160
 0.3805    0.1018
 0.4100    0.0943
 0.4395    0.0868
 0.5186    0.0690
 0.5981    0.0524
 0.6978    0.0341
 0.7901    0.0203
 0.8949    0.0082
 0.9540    0.0031
 1.0000    0.0000

 0.0000    0.0000
 0.0048    -.0152
 0.0106    -.0208
 0.0240    -.0237
 0.0459    -.0273
 0.1069    -.0366
 0.1652    -.0399
 0.2090    -.0397
 0.2632    -.0377
 0.3193    -.0344
 0.3972    -.0281
 0.4171    -.0263
 0.4374    -.0243
 0.5200    -.0164
 0.6044    -.0089
 0.6914    -.0027
 0.7800    0.0023
 0.8917    0.0042
 0.9579    0.0026
 1.0000    0.0000
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Lednicer format dat file
Selig format dat file

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Polars for STRAND AIRFOIL (strand-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   strand-il50,00095.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   strand-il50,00058.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   strand-il100,00097.5 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   strand-il100,000514.2 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   strand-il200,000915.5 at α=15.75°Mach=0 Ncrit=9Xfoil predictionDetails
   strand-il200,000526.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   strand-il500,000992.4 at α=13°Mach=0 Ncrit=9Xfoil predictionDetails
   strand-il500,0005101.6 at α=11.5°Mach=0 Ncrit=5Xfoil predictionDetails
   strand-il1,000,0009141.7 at α=11.75°Mach=0 Ncrit=9Xfoil predictionDetails
   strand-il1,000,0005147.1 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
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