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In this Reaserch we have performed CFD simulation of various shape of missile nose cone. This studied the numerical analysis of a typical nose of the missile with conventional geometry which can be used for various purposes like surface to air missile, air to air missile, air to surface missile, etc. Here our main goal is to obtain the thermal behavior and heat transfer rate over a different nose shape of the missile with the flow pattern along with lowest possible drag. Here we have analyzed the 6 types of missile nose shape such as CONICAL, POWER SERIES, TANGENT OGIVE, ELLIPTICAL, PARABOLIC, HAACK SERIES i.e. Von Karman and the optimized new design. And the results of these nose shapes are compared with the test data provided by client.
A multiphase framework for numerical aero-thermal analysis, based modeling, meshing and simulation has been done for predicting the thermal and aerodynamic behavior on the different nose profile for the missile due to aerodynamic loading at a high speed. However the thermal effects over missile nose structure during operation of supersonic flights was conducted for Mach number M = 2.0,M = 2.0, M = 2.5,M = 3.0 at A=0, and altitude 0.5km from sea level. The results we obtained from the simulation showed us best match results with the test data available and can be used for design and development of new missile.