Document Type : Original Article
Authors
1 Aerospace Engineering Faculty, Shahid Sattari Aeronautical University of Science and Technology , Tehran, Iran
2 Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran
3 Aerospace Research Institute, Tehran, Iran
4 Tarbiat Modares University
Abstract
In this research, a numerical investigation of the steady flow around an air-to-surface missile has been done using Fluent and Missile Datcom software at different speeds and angles of attack. Force and moment coefficients and contours of Mach number, pressure and temperature around the missile have been investigated. In order to reduce the numerical error of the grid, the flow in the critical aerothermal conditions is examined around the nose of the missile using a structured mesh. The results show that the missile has static stability at all speeds and a vortical flow is formed on the body and control surfaces, and with the increase of the angle of attack, these vortices become larger and cover more areas of the body and control surfaces. Examining the temperature distribution on the surface of the missile showed that the point of maximum temperature is located at the tip of the missile and at the leading edge of the control surfaces, and with the increase of the angle of attack, this point inclines towards the bottom of the missile tip. Also, with the increase of Mach number, the temperature value at this point increases. The temperature distribution on the surface of the missile in steady conditions showed that these conditions are equivalent to a very long flight of the missile with the maximum Mach number of 3.7.
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