naca-tn-2435
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- December 15, 2016 Create Date
- December 15, 2016 Last Updated
National Advisory Committee for Aeronautics, Technical Notes - Direct Reading Design Charts for 75S-T6 Aluminum Alloy Flat Compression Panels Having Longitudinal Extruded Z-Section Stiffeners
Direct-reading design charts are presented for 75S-T6 aluminum-
alloy flat compression panels having longitudinal extruded Z-section
stiffeners. These charts, which cover a wide range of proportions,
make possible the direct determination of the stress and all panel
dimensions required to carry a given intensity of loading with a given
skin thickness and effective length of panel.
Design charts for wing compression panels have been presented in
several different forms (see, for example, references 1 and 2) and have
evolved over a period of years into the form presented in reference 3.
This form.permitted the direct selection of the various panel propor—
tions which meet given values of the principal design conditions -
intensity of loading, skin thickness, and effective length of panel.
This form also made possible the ready determination of the proportions
having minimum weight to meet these conditions.
In the present paper, direct-reading design charts similar to those
of reference 3 are presented. These charts are based on the extensive
test data contained in references h and 5 for 758-T6 aluminum-alloy
flat compression panels having longitudinal extruded Z-section stiffeners.
The proportions covered vary from panels in which the stiffeners are
relatively large, thick, and closely spaced (fig. 1) to panels in which
the stiffeners are relatively thin compared to the skin and are small
and widely spaced (fig. 2).
| File | Action |
|---|---|
| naca-tn-2435 Direct Reading Design Charts for 75S-T6 Aluminum Alloy Flat Compression Panels Having Longitudinal Extruded Z-Section S.pdf | Download |
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