Thermal Science 2017 Volume 21, Issue 6 Part B, Pages: 3037-3049
https://doi.org/10.2298/TSCI160919318O
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Numerical aerodynamic-thermal-structural analyses of missile fin configuration during supersonic flight conditions
Ognjanović Ognjen V. (Military Technical Institute, Belgrade)
Maksimović Stevan M. (Military Technical Institute, Belgrade)
Vidanović Nenad D. (Faculty of Transport and Traffic Engineering, Belgrade)
Šegan Stevo D. (Faculty of Mathematics, Belgrade)
Kastratović Gordana M. (Faculty of Transport and Traffic Engineering, Belgrade)
Attention in this work is focused on aerodynamic heating and
aero-thermo-mechanical analysis of fin type structures on the missile at
supersonic flight. 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 (M = 2.3 and M = 3.7). Own available structural
experimental results have been used for computational structural mechanics
(CSM) validation and verification, in order to assure credibility of
numerical fluid-thermal-structure interaction (FTSI). Conducted simulations
were carried out to better understand the FTSIs of the missile fin during
supersonic flight.
Keywords: missile fins, supersonic flight, aerodynamic heating, fluid-thermal-structure interaction