Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation
Апстракт
This paper presents modcation of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and computational fluid dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute in order to determine the final geometry of the new front parts. The 3-D Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force, and pitching moment coe...fficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with.
Кључне речи:
wind tunnel testing / missile model computational fluid dynamics / experimental aerodynamics / aerodynamic coefficientsИзвор:
Thermal Science, 2017, 21, 3, 1543-1554Издавач:
- Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd
DOI: 10.2298/TSCI150515184O
ISSN: 0354-9836
WoS: 000404946100035
Scopus: 2-s2.0-85025464967
Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Ocokoljić, Goran AU - Rašuo, Boško AU - Bengin, Aleksandar PY - 2017 UR - https://machinery.mas.bg.ac.rs/handle/123456789/2601 AB - This paper presents modcation of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and computational fluid dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute in order to determine the final geometry of the new front parts. The 3-D Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force, and pitching moment coefficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with. PB - Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd T2 - Thermal Science T1 - Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation EP - 1554 IS - 3 SP - 1543 VL - 21 DO - 10.2298/TSCI150515184O ER -
@article{ author = "Ocokoljić, Goran and Rašuo, Boško and Bengin, Aleksandar", year = "2017", abstract = "This paper presents modcation of the existing guided missile which was done by replacing the existing front part with the new five, while the rear part of the missile with rocket motor and missile thrust vector control system remains the same. The shape of all improved front parts is completely different from the original one. Modification was performed based on required aerodynamic coefficients for the existing guided missile. The preliminary aerodynamic configurations of the improved missile front parts were designed based on theoretical and computational fluid dynamics simulations. All aerodynamic configurations were tested in the T-35 wind tunnel at the Military Technical Institute in order to determine the final geometry of the new front parts. The 3-D Reynolds averaged Navier-Stokes numerical simulations were carried out to predict the aerodynamic loads of the missile based on the finite volume method. Experimental results of the axial force, normal force, and pitching moment coefficients are presented. The computational results of the aerodynamic loads of a guided missile model are also given, and agreed well with.", publisher = "Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd", journal = "Thermal Science", title = "Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation", pages = "1554-1543", number = "3", volume = "21", doi = "10.2298/TSCI150515184O" }
Ocokoljić, G., Rašuo, B.,& Bengin, A.. (2017). Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation. in Thermal Science Univerzitet u Beogradu - Institut za nuklearne nauke Vinča, Beograd., 21(3), 1543-1554. https://doi.org/10.2298/TSCI150515184O
Ocokoljić G, Rašuo B, Bengin A. Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation. in Thermal Science. 2017;21(3):1543-1554. doi:10.2298/TSCI150515184O .
Ocokoljić, Goran, Rašuo, Boško, Bengin, Aleksandar, "Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation" in Thermal Science, 21, no. 3 (2017):1543-1554, https://doi.org/10.2298/TSCI150515184O . .