Projeto do cone de nariz de um foguete experimental usando software de CFD comercial

Abstract

The aerodynamic evaluation in the design of a rocket is of extreme importance because it dictates the relationship between the rocket and the atmospheric air, and consequently has a great impact on the resulting forces during the flow. Four nose geometries were evaluated, aiming to define one for the development of an experimental rocket with the objective of reaching 3 kilometers of altitude carrying a payload of 4 kilograms, requirements to participate in the IREC, an international competition for the development of rockets. This objective was measured using numerical simulations in ANSYS Fluent, where the fluid considered was air, modeled as an ideal gas, and the flow was considered as a permanent, viscous, compressible regime with constant properties. The problem was modeled as twodimensional and axisymmetric. The averaged Reynolds equations were used to solve the problem using the SST turbulence model. As result, LD-HAACK was proven to be the most efficient for speeds between Mach 0.3 and 1.2, among the analyzed formats.