Bunkley, J. A., & Caballes, M. J. L. O., & Ajuwon, M., & Chen, G. (2022, April), Design Analysis of Rocket Tail Fins Aimed at Higher Apogee by Computer Simulation  Paper presented at 2022 Spring ASEE Middle Atlantic Section Conference, Newark, New Jersey. 10.18260/1-2--40047

\bibitem{asee_peer_40047}
  Bunkley, J. A., \& Caballes, M. J. L. O., \& Ajuwon, M., \& Chen, G. (2022, April), \emph{Design Analysis of Rocket Tail Fins Aimed at Higher Apogee by Computer Simulation}
  Paper presented at 2022 Spring ASEE Middle Atlantic Section Conference, Newark, New Jersey.
  10.18260/1-2--40047

Justyn Allen Bunkley, Marc J Louise O. Caballes, Margaret Ajuwon, and Guangming Chen.  "Design Analysis of Rocket Tail Fins Aimed at Higher Apogee by Computer Simulation".  2022 Spring ASEE Middle Atlantic Section Conference, Newark, New Jersey, 2022, April.  ASEE Conferences, 2022.  https://peer.asee.org/40047 Internet.  07 Jul, 2024

\bibitem{asee_peer_40047}
  Justyn Allen Bunkley, Marc J Louise O. Caballes, Margaret Ajuwon, and Guangming Chen.
  "Design Analysis of Rocket Tail Fins Aimed at Higher Apogee by Computer Simulation".
  \emph{2022 Spring ASEE Middle Atlantic Section Conference, Newark, New Jersey, 2022, April}.
  ASEE Conferences, 2022.
  https://peer.asee.org/40047 Internet.  07 Jul, 2024

@INPROCEEDINGS{asee_peer_40047
author = "Justyn Allen Bunkley, Marc J Louise O. Caballes, Margaret Ajuwon, and Guangming Chen"
title = "Design Analysis of Rocket Tail Fins Aimed at Higher Apogee by Computer Simulation"
booktitle = "2022 Spring ASEE Middle Atlantic Section Conference"
year = "2022"
month = "April"
address = "Newark, New Jersey"
publisher = "ASEE Conferences"
note = {https://peer.asee.org/40047}
number = {10.18260/1-2--40047}
}

TY  - CPAPER
AB  - The rocketry team at a mid-size University is developing a single-stage liquid-propellant rocket (LPR) with a targeted apogee of 13,000 feet. Due to the complexity of the LPR, each component of the rocket must be studied to optimize parameters that play a role in achieving the design apogee. These parameters do so either directly or by affecting other parameters in the optimization space. A wide variety of research papers and peer-reviewed journals that deal with the rocket nose cone and the characteristics of its airframe are already publicly accessible. However, only a few in-depth studies specifically address the design of the rocket's tail fins. Thus, this paper focuses on how different factors, such as the planform shape of the fins – clipped delta and trapezoidal; fin materials – carbon fiber, aluminum, and fiberglass; and its geometric dimensions – root chord and sweep angle, will affect the estimated apogee of a rocket and what is an ideal combination of design parameters. The simulation results collected using the software OpenRocket Simulator shows the possible outcomes of the rocket’s apogee. Furthermore, a factorial design methodology was employed using the collected data and the Minitab software to perform statistical analysis to determine the significant factors and generate surface and contour plots. From the data in the study, the best rocket tail fin design for apogee was determined to be three clipped delta-shaped tail fins made of fiberglass.

Keywords: Liquid-Propellant Rocket (LPR), Apogee, OpenRocket Simulator, Minitab, Design of Experiments (DOE), Rocket Fin

AU  - Justyn Allen Bunkley
AU  - Marc J Louise O. Caballes
AU  - Margaret Ajuwon
AU  - Guangming Chen
CY  - Newark, New Jersey
DA  - 2022/04/22
PB  - ASEE Conferences
TI  - Design Analysis of Rocket Tail Fins Aimed at Higher Apogee by Computer Simulation
UR  - https://peer.asee.org/40047
DO  - 10.18260/1-2--40047
ER  -