Shear Buckling of Flat Plates

This page provides the chapters on shear buckling of flat plates from the "Stress Analysis Manual," Air Force Flight Dynamics Laboratory, October 1986.

Other related chapters from the Air Force "Stress Analysis Manual" can be seen to the right.


a = plate length
b = plate width
E = modulus of elasticity
Es = secant modulus
Et = tangent modulus
f = ratio of cladding thickness to total plate thickness
F0.7F0.85 = secant yield stress at 0.7E and 0.85E
Fcrs = critical shear stress
Fpl = stress at proportional limit
ks = shear buckling coefficient
n = shape parameter, number of half waves in buckled plate
ss = simply supported
t = thickness
W = total load, potential energy
β = ratio of cladding yield stress to core stress
ϵ = ratio of rotational rigidity of plate edge stiffeners
η = plasticity reduction factor
η = cladding reduction factor
λ = buckle half wavelength
ν = inelastic Poisson's ratio
νe = elastic Poisson's ratio

6.5 Shear Buckling of Flat Plates

The critical shear-buckling stress of flat plates may be found from Equation (6-27).

$$ F_{crs} = \eta ~\overline{\eta} ~{ k_s ~\pi^2 E \over 12 (1 - \nu_e)^2 } \left({t \over b}\right)^2 $$

Figure 6-27 presents the shear coefficient ks, as a function of the size ratio a/b for clamped and hinged edges. For infinitely long plates, Figure 6-28 presents ks as a function of λ/b. Figure 6-29(a) presents ks∞ for long plates as a function of edge restraint, and Figure 6-29(b) gives ks∞ as a function of b/a, thus allowing the determination of ks.

The nondimensional chart in Figure 6-30 allows the calculation of inelastic shear buckling stresses if the secant yield stress, F0.7, and n the shape parameter is known (Table 6-11).

The plasticity-reduction factor η and the clodding factor η can be obtained from Equations (6-28), (6-29), and (6-30).

$$ \eta = { E_s \over E } \left({ 1 - \nu_e^2 \over 1 - \nu^2 }\right) $$
$$ \eta = { 1 + 3 f \beta \over 1 + 3 f } ~\text{ for } F_{c1} \lt F_{crs} \lt F_{pl} $$
$$ \eta = {1 \over 1+3f} { \left[1 + 3f \left( { \overline{E_s} \over E_s } \right) \right] + \left\{ \left[1 + 3f \left( { \overline{E_s} \over E_s } \right) \right] \left[ {1 \over 4} + {3 \over 4} \left( E_t \over E_s \right) + W \right] \right\}^{1/2} \over 1 + \left[ {1 \over 4} + {3 \over 4} \left( E_t \over E_s \right) \right]^{1/2} } $$

for Fcrs > Fpl

Shear-Buckling-Stress Coefficient of Plates as a Function of a/b for Clamped and Hinged Edges

Shear-Buckling-Stress Coefficient for Plates Obtained From Analysis of Infinitely Long Plates for Various Amounts of Edge Rotational Restraint

Curves for Estimation of Shear-Buckling Coefficient of Plates with Various Amounts of Edge Rotational Restraint

Chart of Nondimensional Shear Buckling Stress for Panels with Edge Rotational Restraint

Table 6-11: Values of Shape Parameter n for Several Engineering Materials
n Material
3 One-fourth hard to full hard 18-8 stainless steel
One-fourth hard 18-8 stainless steel, cross grain
5 One-half hard and three-fourths hard 18-8 stainless steel, cross grain
10 Full hard 18-8 stainless steel, cross grain
2024-T and 7075-T aluminum-alloy sheet and extrusion
2024R-T aluminum-alloy sheet
20 to 25 2024-T80, 2024-T81, and 2024-T86 aluminum alloy sheet
2024-T aluminum-alloy extrusion
SAE 4130 steel heat-treated up to 100,000 psi ultimate stress
2014-T aluminum-alloy extrusions
SAE 4130 steel heat-treated above 125,000 psi ultimate stress