So that the x-coordinate of the surface at chord position x is slightly perturbed. The coordinates are calculated perpendicular to the line of camber. Returned in a four-element array containing coordinates. evaluate: function(x): The coordinates of the surface at position x.leadingEdgeRadius: function(): The radius of curvature of the leading edge.camberLineSlope: function(x): The slope of the camber line at position x.camberLine: function(x): The height of the camber line above the centerline at position x.thickness: function(x): The half-thickness of the airfoil above or below the camber line at position x.The object returned contains the following functions: chordLength (optional, default = 1): The chord length of the airfoil.The final two digits are the thickness of the airfoil in units of 1% of the chord length. The second digit is the location of maximum camber measured from the leading edge in units of 10% of the chord length. The first digit is the amount of camber in units of 1% of the chord length. nacaAirfoilCode: A four-digit string containing the NACA airfoil code. ![]() ![]() ![]() Parses the airfoil code and returns an object with functions that evaluate the shape of the airfoil for a unit chord length. $ npm install naca-four-digit-airfoil API Based on NACA Code require('naca-four-digit-airfoil')(nacaAirfoilCode)
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