Commit 65a7c9ea by 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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