Author(s):
1. Stevan Maksimović, Serbia
2. Ognjen Ognjanović, Serbia
3. Nenad Vidanović, Serbia
4. Gordana Kastratović, Serbia
5. Katarina Maksimović, Serbia

Abstract:
Attention in this work is focused on aerodynamic heating and aero-thermo-mechanical analysis of fin type structures on the missile at supersonic flight. The modeling of aerodynamic heating of supersonic and hypersonic flights has been under intensive consideration in recent years. At high Mach number the heat due to friction between body and flow, i.e. viscous heating must be taken into account because the velocity field is coupled with the temperature field. The flow field around the fins of the missile and especially the temperature distribution on its surface, as well as aerodynamic-thermal/structural analyses are numerically modeled in ANSYS Workbench environment. The investigation was carried out for two Mach numbers. Available structural experimental results have been used for computational structural mechanics validation and verification, in order to assure credibility of numerical fluid-thermal-structure interaction. In this work a multidisciplinary framework for numerical aerodynamic-thermal/structural analyses, based on only one multi-module software, was used to analyse thermal effects on fin structure during supersonic flights conditions.

Key words:
aerodynamic, aero-thermo-mechanical analysis, numerical modelling, ANSYS, structural analysis

Thematic field:
Mechanics and Design

Date of abstract submission:
24.02.2017.

Conference:
13th International Conference on Accomplishments in Mechanical and Industrial Engineering

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