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  pdftitle={OpenRocket technical documentation},
  pdfauthor={Sampo Niskanen},
  pdfsubject={Technical documentation of the OpenRocket simulation software},
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\begin{document}

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\begin{center}
{\LARGE\bf OpenRocket technical documentation}

{\large For OpenRocket version 1.0.0}

\vspace{-3mm}
2010-04-06

\vspace{10mm}
{\Large Sampo Niskanen}


\vspace{80mm}
Based on the Master's thesis \cite{thesis}

\vspace{-1mm}
\mbox{\hspace{-6pt}
\large\it Development of an Open Source model rocket simulation software}

\end{center}

\vfill


\clearpage
\thispagestyle{empty}

\mbox{}
\vfill

\begin{center}
{\Large\bf Thesis or technical documentation?}
\end{center}

The OpenRocket simulation software was originally developed as the
Master's thesis project of Sampo Niskanen, including its written
part
{\it ``Development of an Open Source model rocket simulation software''}
\cite{thesis}.  The thesis is used as the basis of this technical
documentation, which is updated to account for later development in the
software.  This document often still refers to itself as a thesis, as
no systematic updating of this fact has yet been performed.

While the original thesis is available online under a Creative Commons
no-derivatives license, this document is available under a freer
share-alike license.

\vspace{10mm}

\begin{center}
{\Large\bf Version history}
\end{center}

\begin{center}
\begin{tabular}{lp{120mm}}
2010-04-06 & Initial revision.  Updates the roll angle effect on three- and
four-fin configurations in Section~\ref{update-roll-angle}.
(OpenRocket software 1.0.0)
\end{tabular}
\end{center}

\vfill



%%%%%  Quotation


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\mbox{}
\vfill
{\it ``No. Coal mining may be your life, but it's not mine. I'm never
  going down there again. I wanna go into space.''}
\vspace{5mm}

\hspace{10mm}\parbox{130mm}{
Amateur rocketeer Homer Hickam, Jr. in the movie October Sky (1999), based
on a true story.\\

Hickam later became an engineer at NASA, working in spacecraft design
and crew training.}
\vfill



%%%%%%%%


\tableofcontents

%\listoffigures
%
%\listoftables

\newpage
\section*{List of symbols and abbreviations}

{\bf Symbols}
\nopagebreak

\begin{tabular}{p{20mm}p{105mm}}

$A$           & Area \\
\Afin         & Area of one fin \\
$A_{\rm plan}$& Planform area \\
\Aref         & Reference area \\
$A_{\rm wet}$ & Wetted area \\
$\AR$         & Aspect ratio of a fin, $2s^2/\Afin$ \\
$c$           & Speed of sound \\
$\bar c$      & Mean aerodynamic chord length of a fin \\
$c(y)$        & Chord length of a fin at spanwise position $y$ \\

$C_A$         & Axial drag force coefficient \\
$C_D$         & Drag force coefficient \\
$C_f$         & Skin friction drag coefficient \\
$C_l$         & Roll moment coefficient \\
$C_{ld}$      & Roll damping moment coefficient \\
$C_{lf}$      & Roll forcing moment coefficient \\

$C_m$         & Pitch moment coefficient \\
\Cma          & Pitch moment coefficient derivative, 
                $\frac{\partial C_m}{\partial \alpha}$ \\

$C_N$         & Normal force coefficient \\
\CNa          & Normal force coefficient derivative,
                $\frac{\partial C_N}{\partial \alpha}$ \\

$d$           & Reference length, the rocket diameter \\
$D$           & Drag force \\
$f_B$         & Rocket fineness ratio, $L/d$ \\
$L$           & The rocket length \\
$m$           & Pitch moment \\
$M$           & Mach number \\
$N$           & Normal force; Number of fins \\
$p$           & Air pressure \\
$r(x)$        & Body or component radius at position $x$ \\
$R$           & Reynolds number \\
$s$           & Spanwise length of one fin \\
$T$           & Air temperature \\
$V$           & Volume \\
$v_0$         & Free-stream velocity \\
$x$, $X$      & Position along the rocket centerline \\
$y$           & Spanwise position \\
\end{tabular}

\begin{tabular}{p{20mm}p{105mm}}
$\alpha$      & Angle of attack \\
$\beta$       & $\sqrt{|M^2-1|}$ \\
$\gamma$      & Specific heat ratio, for air $\gamma=1.4$ \\
$\Gamma_c$    & Fin midchord sweep angle \\
$\delta$      & Fin cant angle \\
$\eta$        & Airflow inclination angle over a fin \\
$\theta$      & Roll angle \\
$\Lambda$     & Dihedral angle between a fin and the direction of airflow \\
$\nu$         & Kinematic viscosity of air \\
$\xi$         & Distance from rotation axis \\
$\rho$        & Density of air \\
$\omega$      & Angular velocity \\

\end{tabular}

\vspace{10mm}
{\bf Abbreviations}
\nopagebreak

\begin{tabular}{p{20mm}p{105mm}}
CFD & Computational fluid dynamics \\
CG  & Center of gravity \\
CP  & Center of pressure \\
LE  & Leading edge \\
MAC & Mean aerodynamic chord \\
RK4 & Runge-Kutta 4 integration method \\
UI  & User interface \\
\end{tabular}




\pagebreak
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\include{chapter-introduction}
\include{chapter-basics-of-model-rockets}
\include{chapter-aerodynamic-properties}
\include{chapter-flight-simulation}
\include{chapter-software}
\include{chapter-experimental}
\include{chapter-conclusion}


\clearpage
\vspace*{1cm}
\section*{Acknowledgments}

I would like to express my deepest gratitude to M.Sc.~Timo Sailaranta
for his invaluable advice and consultation on the aerodynamic
simulation of rockets.  Without his input the creation of this thesis
would have been exceedingly laborious.  I would also like to thank
Prof.~Rolf Stenberg for supervising the writing of this thesis, and
Juhani Talvela for proofreading and commenting early versions of this
text.

I am also deeply grateful for my parents Jouni and Riitta, my entire
family, friends and teachers, who have always encouraged me onwards in
my life and studies.  Above all I would like to thank my brother,
Antti~J. Niskanen, for being an inspiration throughout my life and
also for
building the magnetometer logger used in the experimental flights; and
my fiancée Merli Lahtinen, for her patience and loving understanding
for my passion towards rocketry.




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% Chap II - Skin-friction drag
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\appendix

\include{chapter-appendices}




\end{document}
