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BOEING 737 ROOT AIRFOIL (b737a-il)

BOEING 737 ROOT AIRFOIL - Boeing Commercial Airplane Company model 737 airfoils


Airfoil b737a-il
Details Dat file Parser  
(b737a-il) BOEING 737 ROOT AIRFOIL
Boeing Commercial Airplane Company model 737 airfoils
Max thickness 15.4% at 19.6% chord.
Max camber 0.2% at 5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
BOEING 737 ROOT AIRFOIL
       23.       23.

  0.000000  0.017700
  0.002300  0.030900
  0.005000  0.037200
  0.007600  0.041500
  0.014300  0.049900
  0.024900  0.058200
  0.049500  0.073000
  0.074000  0.081400
  0.099000  0.086600
  0.153000  0.090700
  0.196100  0.090500
  0.250400  0.088700
  0.309400  0.085800
  0.352000  0.083300
  0.391900  0.080400
  0.447700  0.075600
  0.503400  0.069600
  0.559300  0.062600
  0.596500  0.057500
  0.648800  0.049800
  0.835100  0.022400
  0.910900  0.013200
  1.000000  0.000300

  0.000000  0.017700
  0.002200  0.003800
  0.004900 -0.001800
  0.007200 -0.005300
  0.011900 -0.010600
  0.024300 -0.020400
  0.048600 -0.034200
  0.071600 -0.045700
  0.097900 -0.051600
  0.148800 -0.060700
  0.195300 -0.063200
  0.250100 -0.063200
  0.294500 -0.062600
  0.357900 -0.061000
  0.396500 -0.059500
  0.454300 -0.056300
  0.505000 -0.052700
  0.555600 -0.048200
  0.606300 -0.042700
  0.648500 -0.037500
  0.831700 -0.014900
  0.941000 -0.005300
  1.000000 -0.000300
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Lednicer format dat file
Selig format dat file

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Polars for BOEING 737 ROOT AIRFOIL (b737a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   b737a-il50,000916.4 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   b737a-il50,000519.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   b737a-il100,000923.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   b737a-il100,000530.3 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   b737a-il200,000938.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   b737a-il200,000546.9 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   b737a-il500,000967.7 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   b737a-il500,000568.3 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   b737a-il1,000,000985.7 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   b737a-il1,000,000579.3 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
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