Aerodynamic Shape Optimization System of a Canard-Controlled Missile Using Trajectory-Dependent Aerodynamic Coefficients

Yang, Young Rok; Jung, Sung-Ki; Cho, Tae Hwan; Myong, R.S.

doi:10.2514/1.57430

Cited by 2 publications

(1 citation statement)

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“…20 and 21 the results for possible combinations of our project target can be seen. For known derivatives of the pitching moment and normal force coefficients ratio of the original missile and assumed required derivatives of the same ratio are determined by changing the wing dimensions and its locations [18][19][20][21][22][23][24][25][26][27]. By varying the shape of the missile models, different values of the derivatives of the normal force and pitching moment coefficients are obtained.…”

Section: Discussionmentioning

confidence: 99%

Aerodynamic shape optimization of guided missile based on wind tunnel testing and computational fluid dynamics simulation

2017

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Original scientific paper https://doi.org/10.2298/TSCI150515184OThis paper presents modification 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.

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