Commit 65a7c9ea authored by Olivier's avatar Olivier

Exercises 7: general clean-up

parent 1a6be0d7
......@@ -22,7 +22,7 @@
F_\text{sphere} &=& 3 \pi \mu U D \ztag{\ref{eq_drag_creeping_sphere}}
\end{IEEEeqnarray}
\Cref{fig_viscosities} quantifies the viscosity of various fluids.
\Cref{fig_viscosities} quantifies the viscosity of various fluids as a function of temperature.
\end{boiboite}
\begin{figure}[h]
......@@ -31,7 +31,7 @@
\includegraphics[width=0.9\textwidth]{images/viscosities_horizontal.jpg}
\vspace{-0.5cm}
\end{center}
\supercaption{Viscosity of various fluids at a pressure of \SI{1}{\bar} (in practice viscosity is almost independent of pressure).}{Figure \copyright\xspace White, 2011, \textit{Fluid Mechanics}, 7th ed. pub. McGraw-Hill}
\supercaption{Viscosity of various fluids at a pressure of \SI{1}{\bar} (in practice viscosity is almost independent of pressure).}{Figure \copyright\xspace White 2008 \cite{white2008}}
\label{fig_viscosities}
\end{figure}
......
......@@ -194,10 +194,10 @@
Based on this work, it can be shown that for a laminar boundary layer flowing along a smooth wall, the four parameters about which we are interested are solely function of the distance-based Reynolds number $\rex$:
\begin{IEEEeqnarray}{rCl}
\frac{\delta}{x} &=& \frac{\num{4,91}}{\sqrt{\rex}} \IEEEyessubnumber\\\nonumber\\
\frac{\delta^*}{x} &=& \frac{\num{1,72}}{\sqrt{\rex}} \IEEEyessubnumber\\\nonumber\\
\frac{\theta}{x} &=& \frac{\num{0,664}}{\sqrt{\rex}} \IEEEyessubnumber\\\nonumber\\
c_{f_{(x)}} &=& \frac{\num{0,664}}{\sqrt{\rex}} \IEEEyessubnumber
\frac{\delta}{x} &=& \frac{\num{4,91}}{\sqrt{\rex}} \IEEEyessubnumber\label{eq_delta_lam}\\\nonumber\\
\frac{\delta^*}{x} &=& \frac{\num{1,72}}{\sqrt{\rex}} \IEEEyessubnumber\label{eq_deltastar_lam}\\\nonumber\\
\frac{\theta}{x} &=& \frac{\num{0,664}}{\sqrt{\rex}} \IEEEyessubnumber\label{eq_deltastarstar_lam}\\\nonumber\\
c_{f_{(x)}} &=& \frac{\num{0,664}}{\sqrt{\rex}} \IEEEyessubnumber\label{eq_cf_lam}
\end{IEEEeqnarray}
%%%%%%%%%%%%%%%%%
......@@ -291,10 +291,10 @@
In the same way that we have worked with the laminar boundary layer profiles, we can derive models for our characteristics of interest from this velocity profile:
\begin{IEEEeqnarray}{rCl}
\frac{\delta}{x} &\approx& \frac{\num{0,16}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\\\nonumber\\
\frac{\delta^*}{x} &\approx& \frac{\num{0,02}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\\\nonumber\\
\frac{\theta}{x} &\approx& \frac{\num{0,016}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\\\nonumber\\
c_{f_{(x)}} &\approx& \frac{\num{0,027}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber
\frac{\delta}{x} &\approx& \frac{\num{0,16}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\label{eq_delta_turb}\\\nonumber\\
\frac{\delta^*}{x} &\approx& \frac{\num{0,02}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\label{eq_deltastar_turb}\\\nonumber\\
\frac{\theta}{x} &\approx& \frac{\num{0,016}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\label{eq_deltastarstar_turb}\\\nonumber\\
c_{f_{(x)}} &\approx& \frac{\num{0,027}}{\rex^{\frac{1}{7}}} \IEEEyessubnumber\label{eq_cf_turb}
\end{IEEEeqnarray}
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
\section{Separation}
......
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......@@ -156,3 +156,12 @@
isbn= {0486434850},
language= {english},
}
@book{abbottvondoenhoff1959,
title= {Theory of wing sections, including a summary of airfoil data},
author= {Abbott, Ira Herbert and Von Doenhoff, Albert Edward},
year= {1959},
publisher= {Courier},
language= {english},
}
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