# Question p.23.5: The idealized cross-section of a two-cell thin-walled wing b...

The idealized cross-section of a two-cell thin-walled wing box is shown in Fig. P.23.5. If the wing box supports a load of 44 500 N acting along the web 25, calculate the shear flow distribution. The shear modulus G is the same for all walls of the wing box.

$\begin{array}{llllc}\hline \text { Wall } & \text { Length }(\mathrm{mm}) & \text { Thickness }(\mathrm{mm}) & \text { Boom } & \text { Area }\left(\mathrm{mm}^2\right) \\\hline 16 & 254 & 1.625 & 1,6 & 1290 \\25 & 406 & 2.032 & 2,5 & 1936 \\34 & 202 & 1.220 & 3,4 & 645 \\12,56 & 647 & 0.915 & & \\23,45 & 775 & 0.559 & & \\\text { Cell areas: } A_{\mathrm{I}}=232000 \mathrm{~mm}^2, A_{\mathrm{II}}=258000 \mathrm{~mm}^2 & & \\\hline\end{array}$
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Question: p.23.9

## A portion of a wing box is built-in at one end and carries a shear load of 2000 N through its shear centre and a torque of 1000 N m as shown in Fig. P.23.9. If the skin panel in the upper surface of the inboard bay is removed, calculate the shear flows in the spar webs and remaining skin panels, ...

Consider first the flange loads and shear flows pr...
Question: p.23.8

## A portion of a tapered, three-cell wing has singly symmetrical idealized cross-sections 1000 mm apart as shown in Fig. P.23.8. A bending moment Mx = 1800 N m and a shear load Sy = 12 000 N in the plane of the web 52 are applied at the larger cross-section. Calculate the forces in the booms and the ...

The direct stresses in the booms are given by the ...
Question: p.23.7

## A singly symmetric wing section consists of two closed cells and one open cell (see Fig. P.23.7). The webs 25, 34 and the walls 12, 56 are straight, while all other walls are curved. All walls of the section are assumed to be effective in carrying shear stresses only, direct stresses being carried ...

Referring to Fig. P.23.7 the horizontal x axis is ...
Question: p.23.6

## Figure P.23.6 shows a singly symmetric, two-cell wing section in which all direct stresses are carried by the booms, shear stresses alone being carried by the walls. All walls are flat with the exception of the nose portion 45. Find the position of the shear centre S and the shear flow ...

Referring to Fig. P.23.6, the horizontal x axis is...
Question: p.23.4

## Determine the shear flow distribution for a torque of 56 500 N m for the three cell section shown in Fig. P.23.4. The section has a constant shear modulus throughout. ...

In this problem the cells are not connected consec...
Question: p.23.3

## Determine the torsional stiffness of the four-cell wing section shown in Fig. P.23.3. Data: Wall 12 23 34 78 67 56 45° 45^i 36 27 18 Peripheral length (mm) 762 812 812 1525 356 406 356 254 Thickness (mm) 0.915 0.915 0.915 0.711 1.220 1.625 1.220 0.915 Cell areas (mm²) AI = 161 500 AII = 291 000 ...

From Eq. (23.6) for Cell I \frac{\mathrm{d}...
Question: p.23.2

## Figure P.23.2 shows the cross-section of a two-cell torque box. If the shear stress in any wall must not exceed 140 N/mm², find the maximum torque which can be applied to the box. If this torque were applied at one end and resisted at the other end of such a box of span 2500 mm, ...

From Eq. (23.6) for Cell I \frac{\mathrm{d}...
Question: p.23.1

## The central cell of a wing has the idealized section shown in Fig. P.23.1. If the lift and drag loads on the wing produce bending moments of −120 000 N m and −30 000 N m, respectively at the section shown, calculate the direct stresses in the booms. Neglect axial constraint effects and assume that ...

The beam section is unsymmetrical and M_x=-...
Question: 23.7