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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A Method for Calculating the Subsonic Steady-state Loading on an Airplane with a Wing of Arbitrary Plan Form and Stiffness
A method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors is given. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers. It includes the effects of external stores and fuselage on the spanwise loading. Modifications are outlined for treating tail-boom and tailless airplane configurations and for calculating the divergence dynamic pressure of a swept wing with a large external store. A method is also outlined for reducing wind-tunnel data to obtain effective aerodynamic coefficients which are free of model flexibility effects. The effects of Mach number can readily be evaluated from the aerodynamic coefficients thus obtained.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
language: en
Publisher:
Release Date: 1953