Numerical Simulation of Heat Flux Evaluation for Atmospheric Re-entry Control Wing Connections

Document Type : Research Article

Authors

1 malek ashtar university

2 University of Urmia

Abstract

The present research has investigated the simulation of the aerodynamic heating of a missile with regard to the placement and non-placement of the control block and its connection components. In this research, he investigated four different geometries of a commercialized missile sample, including a missile without a block, a missile with a control block, a missile with a control block and a shaft connected to it, and a missile with a control block and a shaft connected to it, considering the wedge. The results showed that the presence of control block as an obstacle in the way of air flow has increased the heat flux on the missile surface by about 27% compared to the first phase. In the upstream of the shaft, t in the amount of heat flux is 5 times compared to the case without the shaft. Also, with the simulation of the fourth phase, the effect of the presence of the wedge in guiding the fluid flow and reducing the damaging effects of heating around the location of the shaft was revealed. The results showed that the presence of the wedge caused the heat flux of the missile surface to decrease by about 52% compared to the third phase. Also, the wedge has reduced the maximum heat flux created on the shaft surface by about 74% compared to the third phase.

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Amirkabir Journal of Mechanical Engineering
Volume 56, Issue 7
October 2024
Pages 6-6

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