RCAIDE.Library.Methods.Geometry.Planform.compute_segment_volume

compute_segment_volume#

compute_segment_volume(wing, inner_segment, outer_segment, n_points=401)[source]#

Estimate the prism volume between two consecutive wing segments using their airfoil cross-sectional areas and local span.

Parameters:

  • wing (Wing) – Wing object containing reference chord and span information.

  • inner_segment (WingSegment) – Upstream segment with airfoil definition and percent span/chord scaling.

  • outer_segment (WingSegment) – Downstream segment with airfoil definition and percent span/chord scaling.

  • n_points (int, optional) – Number of points to generate NACA 4-series airfoil geometry when missing.

Returns:

Estimated segment volume [m³] using a frustum (prismoid) approximation.

Return type:

float

Notes

  • If airfoil geometry is absent, a NACA 4-series shape is generated/assumed.

  • Areas are computed via polygon integration of the airfoil coordinates.

  • Volume uses (1/3)*(A1 + A2 + sqrt(A1*A2))*span for the local segment span.