Table of Contents

Aerofoil

https://bladednextgen.dnv.com/schema/0.4.1/Components/Blade/AerofoilLibrary/Aerofoil/Aerofoil.json

The definition of a single 2D aerodynamic aerofoil section.

  • ChordwiseOriginForForcesAndMoments: number
  • AerodynamicPerformance: array[object (AlphaLine)]
  • ReynoldsNumber: number
  • ThicknessToChordRatio: number

Properties

ChordwiseOriginForForcesAndMoments: number, optional

The fraction of the chord from the leading edge to the position about which Cl, Cd, and Cm have been calculated. This is traditionally 0.25 (25%), but can be any location so long as it is consistent with the provided aerodynamic data.

default = 0.25

AerodynamicPerformance: array[ object (AlphaLine) ]

The relationship between angle of attack, and the lift and drag coefficients.

ReynoldsNumber: number

The Reynolds number at which the aerodynamic properties were obtained.

ThicknessToChordRatio: number

The ratio between the thickness and the chord length of the measured airfoil.