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B-29 ROOT AIRFOIL (b29root-il)

B-29 ROOT AIRFOIL - Boeing B-29 root airfoil


Airfoil b29root-il
Details Dat file Parser  
(b29root-il) B-29 ROOT AIRFOIL
Boeing B-29 root airfoil
Max thickness 22% at 30.2% chord.
Max camber 1.7% at 30.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
B-29 ROOT AIRFOIL
      19.0      21.0
 
 0.0000000 0.0000000
 0.0082707 0.0233088
 0.0132000 0.0298517
 0.0255597 0.0425630
 0.0503554 0.0603942
 0.0751941 0.0739301
 0.1000570 0.0850687
 0.1498328 0.1023515
 0.1996558 0.1149395
 0.2495240 0.1230325
 0.2994312 0.1272298
 0.3993490 0.1253360
 0.4993711 0.1130538
 0.5994664 0.0934796
 0.6996058 0.0695104
 0.7997553 0.0445423
 0.8998927 0.0207728
 0.9499514 0.0098870
 1.0000000 0.0000000
 
 0.0000000 0.0000000
 0.0061140 -.0208973
 0.0062188 -.0210669
 0.0087532 -.0247377
 0.0138088 -.0307807
 0.0264052 -.0416431
 0.0515127 -.0548774
 0.0765762 -.0637165
 0.1016176 -.0703581
 0.1516652 -.0801452
 0.2016828 -.0869356
 0.2516733 -.0910290
 0.3016387 -.0926252
 0.4015163 -.0905235
 0.5013438 -.0834273
 0.6011363 -.0728351
 0.7008976 -.0591463
 0.8006328 -.0428603
 0.9003380 -.0235778
 0.9501740 -.0122883
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for B-29 ROOT AIRFOIL (b29root-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   b29root-il50,00092.4 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   b29root-il50,00058.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   b29root-il100,000913.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   b29root-il100,000534.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   b29root-il200,000958.2 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   b29root-il200,000552.8 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   b29root-il500,000977.9 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   b29root-il500,000568.8 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   b29root-il1,000,000990.5 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   b29root-il1,000,000583.2 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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