Accession Number:

AD0687165

Title:

VORTEX LATTICE METHOD FOR CALCULATION OF QUASI STEADY STATE LOADINGS ON THIN ELASTIC WINGS IN SUBSONIC FLOW

Descriptive Note:

Corporate Author:

AERONAUTICAL RESEARCH INST OF SWEDEN STOCKHOLM

Personal Author(s):

Report Date:

1966-01-01

Pagination or Media Count:

18.0

Abstract:

Wing systems that contain several wing surfaces are considered. The surfaces are arbitrarily divided in the chordwise and spanwise directions into panels boxes. The panel load is simulated by a horseshoe vortex, and the boundary condition is fulfilled on every panel at one point. For each surface the vortices and the control points are positioned on a wing chord plane. These planes are perpendicular to the y- or z-axis. The incidence distribution or the load distribution may be found from a system of linear equations, when one of these distributions is given. The calculations can be performed for elastic wings, if the elastic properties are known in the form of a deformation matrix. The calculation procedure was programmed for an electronic computer. Good correlation was obtained between the results from this method and those from other lifting surface methods or experiments. Author

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE