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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}
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\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}
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{\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
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\tableofcontents
%\listoffigures
%
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\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 fianc�e Merli Lahtinen, for her patience and loving understanding
for my passion towards rocketry.
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% Practical Information on AERODYNAMICDRAG and HYDRODYNAMIC RESISTANCE
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%
% Chap II - Skin-friction drag
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\appendix
\include{chapter-appendices}
\end{document}