> For the complete documentation index, see [llms.txt](https://docs.aviumtechnologies.com/llms.txt). Markdown versions of documentation pages are available by appending `.md` to page URLs; this page is available as [Markdown](https://docs.aviumtechnologies.com/user-guide/the-configuration-file/calculating-skin-friction.md).

# Calculating skin friction

{% hint style="warning" %}
An improved skin friction algorithm is currently in development.
{% endhint %}

The APM Solver uses the following expression to approximate the skin friction coefficient:

$$
Re\_{ref}=\frac{\rho\_{ref}|\mathbf{V}*{ref}|c*{ref}}{\mu\_{ref}},\\
C\_{f}=\frac{0.455}{log\_{10}(Re\_{ref})^{2.58}}
$$

In the above expression, $$Re\_{ref}$$is the Reynolds number based on the reference chord. Schlichting's relation \[1] is used to obtain the skin friction coefficient from the Reynolds number. The skin friction coefficient is then multiplied by the surface velocity vector at the centre of each panel to approximate the loads resulting from viscosity.

{% hint style="info" %}
To disable the approximation of viscous loads set the dynamic viscosity $$\mu\_{ref}$$to 0. The default APM Solver value for$$\mu\_{ref}$$is $$1.7890\times10^{-5}$$.
{% endhint %}

## References

\[1] Gudmundsson, S., "General Aviation Aircraft Design Applied Methods and Procedures", Ed. 1, 2014, pp. 678-679