![]() ![]() This design method consists of a geometry creation step in which a three-dimensional geometry is generated, a mathematical model presented and a simple flow analysis (FLUENT Simulation from SolidWorks2012 and ANSYS Simulation with SPH for fluid-structure interaction), step which predicts the air intake mass flow rate. The motivation for such a work is caused by a lack of data on aerodynamics for profiles of some nose cones and especially improved aerodynamic qualities that can be used in designing missiles/ rockets. The scope of this paper is to develop some prototype profiles with outstanding aerodynamic qualities and low cost for use in construction projects for missile increasing their range and effect on target. For this complex work, it was necessary to collect and study the various nose cone shapes and the equations describing them? The paper objective was to identify the types of nose cones with ejector channels and specific aerodynamic characteristics of different types of nose cones. It is shown that significant performance gains result from the adaptation of the exhaust flow to the ambient pressure. The conclusions were drawn and the ogival nose shape has the minimum aerodynamic resistance.Ī new nose cones concept that promises a gain in performance over existing conventional nose cones is discussed in this paper. The results obtained were validated within a variation of 10 percent. The aerodynamic properties such as the downstream Mach number, wave angle, pressure ratio, density ratio, temperature ratio and the aerodynamic coefficients were estimated computationally and were simultaneously compared theoretically with the oblique shock theory. The work includes flow characterization of these nose shapes in Ansys Fluent and for the flow being near the wall, K-omega (2 Eq.) Standard model is chosen. ![]() ![]() The research aims to compare the Conical and Ogival nose cone shapes of the supersonic missile at Mach 2.0. The main challenge is that the nose shape being the foremost part of the missile, experiences high aerodynamic loads which must be resisted by the compressible motion of the fluid for optimum performance at supersonic speeds. The selection of the nose shape is considered to be one of the most crucial aspects in designing the missile as the nose cones are designed to travel at different speeds and altitude. ![]()
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