A Method for Calculating the Subsonic Steady-State Loading on an Airplane With a Wing of Arbitrary Plan Form and Stiffness

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Abstract

Note presenting a method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers.

Topics & Keywords

Computational Fluid Dynamics and Aerodynamics Advanced Aircraft Design and Technologies Aerospace and Aviation Technology

UN Sustainable Development Goals

Affordable and clean energy

Publication Details

Published in: University of North Texas Digital Library (University of North Texas)

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