Aerodynamics Design and Optimization of Supersonic 122 mm DTI Rocket by Using Computational Fluid Dynamics

Main Article Content

Wanchai Jiajan
Aekkapol Baipho


The purpose of this paper is to analyze the static and dynamic coefficients of the 122 mm DTI-2 rocket with MRV-U warhead by using Computational Fluid Dynamics (CFD). Optimization method is also employed to design the warhead of DTI-2 rocket for enhancing the range performance in supersonic regimes (Mach 1.5 - 4). The analysis results show that the static and dynamic coefficients are agreed well with the available wind tunnel data. They are within 10% and 15% for static and dynamic coefficients, respectively throughout the whole range of operating Mach number. For the optimization processes coupled with CFD simulation, the optimization result shows that the new warhead design provides lower drag results when compared with the benchmark MRV-U warhead, while remains statically and dynamically stable. The optimum design total drag is reduced about 6%. The reduced drag can be clearly representing the possibility of enhancing the range performance of the optimum design.


Download data is not yet available.

Article Details

How to Cite
W. Jiajan and A. Baipho, “Aerodynamics Design and Optimization of Supersonic 122 mm DTI Rocket by Using Computational Fluid Dynamics”, Def. Technol. Acad. J., vol. 4, no. 10, pp. 90–107, Oct. 2022.
Research Articles


W. Jiajan and N. Sukuprakan, “Aerodynamic Analysis of Supersonic 2.75 inch Fin -Stabilized Rocket using Computational Fluid Dynamics,” NKRAFA J.Sci.Technol., vol. 3, no. 13, pp. 34 - 44, 2017.

Pattarakorn. “สทป. ยิงทดสอบจรวดขนาด 122 มม. (ไม่นำวิถี) ภายใต้โครงการวิจัยและพัฒนา ระบบจรวดสมรรถนะสูงแบบ DTI-2.” &cid=27&cno=6156 (วันที่เข้าถึง ก.ค. 17, 2565).

A. Sumnu, I. H. Guzelbey, and O. Ogucu, “Aerodynamic Shape Optimization of a Missile Using a Multi-objective Genetic Algorithm,” J. Aerosp. Eng., vol. 2020, pp. 1-17, 2020, doi: 10.1155/2020/1528435.

W. Jiajan, R. S. M. Chue, T. Nguyen, and S. Yu, “Optimisation of Round Bodies for Aerodynamic Performance and Stability at Supersonic Speeds,” Aeronaut. J., vol. 117, no. 1193, pp. 661 - 685, 2013.

W. Jiajan, R. S. M. Chue, T. Nguyen, and S. C. M. Yu, “Boattail Juncture Shaping for Spin-stabilized Rounds in Supersonic Flight,” Shock Waves, vol. 25, no. 2, pp. 189 - 204, 2015.

J. DeSpirito, “Effects of Base Shape on Spin-Stabilized Projectile Aerodynamics,” in 26th AIAA Appl. Aerodynamics Conf., Honolulu, Hawaii, 2008.

K. J. Beers, NumericalMethod for Chemical Engineering Applications in MATLAB. New York, USA: Cambridge Univ. Press, 2006.

R. L. McCoy, “MC Drag - A Computer Program for Estimating the Drag Coefficients of Projectiles,” U.S. Army Armament Research & Development Command, MD, USA, Tech. Rep. ARBRL-TR-02293, 1981.

FLUENT, 2016, “FLUENT 16 User’s Guide,” ANSYS, Inc.

F. R. Menter, “Two-Equation Eddy -Viscosity Turbulence Models for Engineering Applications,” AIAA j., vol. 32, no. 8, pp.1598-1650, 1994.

P. Weinacht and W. Sturek, “Navier-Stokes Predictions of Pitch Damping for Finned Projectiles Using Steady Coning Motion,” in Proc. AIAA 8th Appl. Aerodynamics Conf., AIAA, Washington, D.C., USA, 1990, pp. 632 – 642.