If your wood happens to be available in the form of a rectangular panel with constant thickness, then there is a straightforward way to determine the three main stiffnesses of the wood, using vibration resonance frequencies. I will describe the measurement procedure first, then deal with the mathematical background later in the section.

The simplest way to do this test is based on the traditional approach of Chladni patterns. The plate is set into vibration, and powder is sprinkled on it. When you excite a resonance of the plate, the powder bounces vigorously and collects at the nodal lines, thus revealing the mode shape. Ernst Chladni was a German scientist and musician in the 18th and early 19th centuries. He found that he could excite vibration modes of metal plates by bowing the edge. But for a controllable measurement, bowing is not very convenient: these days is better to generate sine waves and play them through a loudspeaker.

Figure 1 shows a typical setup. The loudspeaker is fixed to the underside of a flat bench-top. It is driven by the sine-wave oscillator you can see under the bench. Next to that is a frequency counter, which tells you the frequency you are currently generating (very much like an electronic tuner that you might use to tune an instrument). In the picture, a square plate of plywood is being tested. It is showing a mode shape with a cross-shaped pattern of nodal lines: usually this is the lowest-frequency mode of a panel like this.

Notice how the plate has been arranged. It is being supported by four small pieces of foam, carefully placed underneath the nodal lines. These are not easily visible in Fig. 1, but they are more clear in Fig. 2, which shows a different mode of the same plywood plate. The plate is positioned differently in the two pictures, relative to the loudspeaker. This is deliberate. You need your loudspeaker to be under an antinodal region of the mode shape, and you also want to cover the loudspeaker aperture fairly well so that your sound doesn’t all escape round the edges. In Fig. 2, the loudspeaker is not visible because it is under the centre of the plate. But this position would be no good for the mode in Fig. 1, where the centre is a nodal region. Instead, the speaker is under one corner of the plate, where the vibration is most vigorous.

Figure 3 shows computed predictions of the nodal line patterns for a few modes of a plate like this. The exact details of nodal line shape, and also the frequency order of the modes, depends on the stiffnesses we are trying to measure, but any orthotropic plate with reasonably uniform mechanical properties will have modes looking recognisably like these — with an important exception that we will come to shortly.

Figure 3 tells you something else interesting. With a bit of practice, you can use the knowledge of these nodal line patterns to find at least some of the resonance frequencies by ear. Hold the plate lightly between finger and thumb on a nodal line, tap with your knuckle in a place where the vibration amplitude is large, and place your ear close to the same point. You should hear a “tap tone” that corresponds to the frequency of that mode. At least for the simplest mode shapes, this method can work very well. The complication is that the tap sound you hear contains contributions from all the modes, especially any others with a nodal line close to your holding position. You can probably hear the lowest frequency among these, but it is more difficult to “hear out” the higher ones.

The modes we are most interested in are the three in the top row of Fig. 3. Figures 4, 5 and 6 show Chladni patterns of these three modes for a square spruce plate. For this particular plate, these were modes numbers 1, 2 and 5: two of the modes from the bottom row of Fig. 3 had frequencies lower than the mode in Fig. 6, involving bending along the grain. The node lines in Fig. 6 are somewhat distorted. This is a result of variation of mechanical properties across the plate: you can see that the spacing of the annual rings varies quite a lot. The rings are closely-spaced in the lower third of the plate, then they abruptly get wider apart. Perhaps a neighbour of this tree was felled at that time, letting more light through? But the slight distortion does not stop us identifying the mode we are after.

From the frequencies of these three modes, plus knowledge of the dimensions and weight of the plate, we can calculate stiffnesses associated with twisting, bending across the grain, and bending along the grain, respectively. We will give formulae for this shortly, together with some background theory to explain what these stiffnesses mean. But first we should deal with the exception to the claim that mode shapes like these can usually be found.

It is probably simplest to introduce the key idea by forgetting about wood (temporarily) and thinking about a metal plate, which will have properties that are the same in all directions. Such a plate is called “isotropic”. What will happen if our metal plate is exactly square? Our first guess might be that the two modes corresponding to Figs. 5 and 6 will fall at the same frequency. But in fact something more interesting happens. We do indeed find two modes, fairly close in frequency, but the shapes look quite different from those pictures. Figure 7 shows computer predictions of the node line patterns of these two modes, and Fig. 8 shows them in a 3D view.

These modes are often described as the “X-mode” and the “ring mode”, for obvious reasons. The best way to think about these two shapes is as the *difference* and the *sum* of the two modes we found before. These involved more or less one-dimensional bending in the two directions. Subtracting one from the other generates the diagonal node lines we see on the left in Fig. 7, while adding them together produces the “hill” shape that we see on the right.

These two modes have different frequencies: usually the ring mode is higher in frequency than the X-mode. The reason is to do with something we mentioned earlier, *Poisson’s ratio*. Suppose we did a beam vibration test with a thin rectangular beam of metal. As it bends, the upper surface is stretched while the lower surface is compressed (or vice versa if it bends in the other direction). Think about a small volume of metal near the upper surface. It is being stretched along the beam axis, so Poisson’s ratio requires that it should shrink a little in the perpendicular directions. Conversely, a small volume of metal near the bottom surface is being compressed along the beam axis, so it is expanding a bit in the cross direction.

So the top surface of our beam is shrinking across the width, while the bottom surface is expanding. This combination will make the beam want to bend in the cross direction, with the *opposite sign* to the way the main beam is bending. This effect is sometimes called “anticlastic curvature”. Now return to our X-mode and ring mode of the plate. The X-mode shows strong anticlastic curvature, but the ring mode has the opposite behaviour, “synclastic curvature”. So the X-mode is “going with the flow”, doing what Poisson’s ratio wants, whereas the ring mode is fighting against Poisson’s ratio. The effect is that Poisson’s ratio provides a bit of extra stiffness in the ring mode compared to the X-mode, and that in turn means that it has a higher frequency.

Returning to our spruce plate, something very similar can happen. The only difference is that the plate doesn’t need to be square, it needs to be longer in the grain direction. Specifically, the aspect ratio of the spruce plate must be adjusted to match the proportions you would find if you made long-grain and cross-grain beams which had the same frequency.

Now it is time to introduce the actual stiffness parameters for our plate, and relate them to the mode frequencies we have been talking about. We will use an energy-based approach to define a suitable set of stiffnesses. Back in section 3.3.1 we saw the expressions for energy in a vibrating beam, and we also met Rayleigh’s principle. We now make use of both those ideas. The potential energy of a bending beam was proportional to the squared curvature, and the curvature is the second derivative of the displacement.

We expect a similar expression for our plate: a quadratic expression involving second derivatives in $x$ and $y$, the coordinates along the symmetry axes of the material (and the edges of the plate). Furthermore, we expect this expression to be symmetrical if you interchange $x$ and $y$. There are just four possible expressions satisfying these conditions, so our most general expression for the potential energy must take the form

$$ V = \dfrac{1}{2} \int{\int{h^3 \left[ D_1 \left(\dfrac{\partial^2 w}{\partial x^2} \right)^2 + D_2 \dfrac{\partial^2 w}{\partial x^2} \dfrac{\partial^2 w}{\partial y^2} \right. }} $$

$$ \left. + D_3 \left(\dfrac{\partial^2 w}{\partial y^2} \right)^2 + D_4 \left(\dfrac{\partial^2 w}{\partial x \partial y} \right)^2 \right] dx dy \tag{1}$$

where $w(x,y)$ is the displacement of the plate, $h$ is the thickness, and $D_1$–$D_4$ are four constants with the dimensions of stiffness. The corresponding expression for kinetic energy is much simpler:

$$T=\dfrac{1}{2} \int{\int{ \rho h \left( \dfrac{\partial w}{\partial t} \right)^2 dx dy }} \tag{2}$$

where $\rho$ is the density.

Now we can calculate three simple estimates using Rayleigh’s principle, to obtain approximate expressions for the frequencies of the three modes in the top row of Fig. 3. The first of those three modes involves twisting motion. We can call the frequency (in Hz) $f_t$, and obtain a Rayleigh estimate using the approximate mode shape $w \approx xy .$ The result, turned round to give an expression for stiffness, is

$$D_4 \approx 0.274 f_t^2 \rho a^2 b^2/h^2 \tag{3}$$

where the plate has dimensions $a \times b$. The other two modes in the top row of Fig. 3 involve approximately one-dimensional bending in the $x$ and $y$ directions. If we call the corresponding frequencies $f_x$ and $f_y$, we can obtain Rayleigh estimates for both by using the first mode of a free-free beam as an approximate mode shape. This gives the expressions

$$D_1 \approx 0.0789 f_x^2 \rho a^4/h^2 \tag{4}$$

and

$$D_3 \approx 0.0789 f_y^2 \rho b^4/h^2 . \tag{5}$$

There is a way to improve on these three simple estimates, but it involves more elaborate computation (see [1] for the details). For workshop use by a guitar maker, though, these first estimates are good enough to be useful in quantifying the stiffness properties of their stock of soundboard blanks.

You will have noticed that we do not have an estimate for $D_2$. There is a procedure for finding that, but it involves cutting the plate to the “magic” proportions needed to make the X-mode and ring mode appear. Again, the details are described in [1]. But a guitar maker is unlikely to want to cut their soundboard blanks in this way, so it is fortunate that numerical studies suggest that $D_2$ is not very important, *except* for the special case of a plate cut with the magic proportions.

Finally, we would surely like to relate these stiffness parameters $D_j$ to more standard things such as Young’s moduli and shear moduli. The full story here is rather complicated, though. The only case which gives clear-cut answers is the ideal quarter-cut plate, in which the $x$ and $y$ axes are exactly aligned with the L and R directions in the solid timber. For that case,

$$D_1 = E_L/12 \mu, D_2 = \nu_{LR}E_R/6 \mu = \nu_{RL}E_L/6 \mu, $$

$$D_3 = E_R/12 \mu, D_4 = G_{LR}/3 \tag{6}$$

where $E_L$ and $E_R$ are the two Young’s moduli, $G_{LR}$ is the shear modulus in the LR plane, $\nu_{LR}$ and $\nu_{RL}$ are the two Poisson’s ratios, and $\mu=1 – \nu_{LR} \nu_{RL} .$ The two versions of the expression for $D_2$ make use of the reciprocal relation for Poisson’s ratios. For the full gory details of more general cases, see [1].

Finally, as a guide what kind of numbers you might expect if you measure the $D_j$ for soundboard material, here are some measured results for spruce. A quarter-cut plate gave $D_1=1320 \mathrm{~Mpa}$, $D_2=77 \mathrm{~Mpa}$, $D_3=82 \mathrm{~Mpa}$, $D_4=227 \mathrm{~Mpa}$. For contrast, the spruce plate shown in Fig. 9 of section 10.3, with a ring angle close to $45^\circ$, gave $D_1=880 \mathrm{~Mpa}$, $D_2=24 \mathrm{~Mpa}$, $D_3=13 \mathrm{~Mpa}$, $D_4=229 \mathrm{~Mpa}$.

[1] M. E McIntyre and J. Woodhouse, “On measuring the elastic and damping constants of orthotropic sheet materials”, *Acta Metallurgica* **36**, 1397—1416 (1988).