RCAIDE.Library.Methods.Geometry.Planform.estimate_wing_internal_volume

estimate_wing_internal_volume#

Functions

estimate_wing_internal_volume(wing, m, p)

Computes the volume of a wing with NACA 4-series airfoils.
estimate_wing_internal_volume(wing, m, p)[source]#

Computes the volume of a wing with NACA 4-series airfoils.

Assumptions: Wing has constant thickness to chord along the span Front spar is at 10%chord and rear spar is at 60% chord

Source: Wikipedia, based on Moran, Jack (2003). An introduction to theoretical and

computational aerodynamics. Dover.

Inputs: m [-] percent camber (.1 is 10%) p [-] location of max camber (.1 is 10% along chord) wing.chords.

root [m] tip [m]

wing.taper [-] wing.thickness_to_chord [-] wing.spans.projected [m] chord_length [m]

Outputs: volume [m^3]

Properties Used: N/A