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    Critical Compressive Stress for Outstanding Flanges (1941)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A chart is presented for the values of the coefficient in the formula for the critical compressive stress at which buckling may be expected to occur in outstanding flanges. These flanges are flat rectangular plates supported along the Loaded edges, supported and elastically restrained along one unloaded edge, and free along the other unloaded edge. The mathematical derivations of the formulas required for the construction of the chart are given.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-188
    Format: application/pdf
    Location Call Number Expected Availability
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