ЧИСЛЕННОЕ МОДЕЛИРОВАНИЕ ОБТЕКАНИЯ СПУСКАЕМОГО АППАРАТА ПРИ СВЕРХЗВУКОВЫХ И ГИПЕРЗВУКОВЫХ СКОРОСТЯХ. СРАВНЕНИЕ ДВУХ СПУСКАЕМЫХ АППАРАТОВ. ЧАСТЬ 2

Abstract

This study is a continuation of the first part “Flow simulation over reentry capsule at supersonic and hypersonic speeds. The comparison between two reentry capsules. Part 1”. This study presents a comparison between two reentry capsules, which are made in Russia. Numerical algorithms solve for the CFD method, which is produced using help ANSYS Fluent 19.2. The using GPU core to get a solution faster. The main purpose – flow simulation and numerical analysis two tips reentry capsule understand the behavior of supersonic and hypersonic flow and its effect on the reentry capsule; compare temperature results and compare drag coefficient for the range Mach numbers equals 2–6. This study showed results on velocity counters, on temperature counters and drag coefficient for range Mach numbers equals 2–6. This study demonstrates the importance of understanding the effects of shock waves and illustrates how the shock wave changes as the Mach number increases. For every solves, the mesh had adapted for pressure gradient and velocity gradient to get the exact solution. As a result of the obtained solution, it is found that the “Prototype 2” reentry vehicle has a lower temperature a lateral surface, than the “Prototype 1”, but a higher temperature over the frontal segment at Mach number M = 6. A general trend has been observed, which is that the resistance drag coefficient decreases with increasing Mach number, which is associated with high height and low density and pressure values. The relevance and significance of this problem for the design of new and modernization of old reentry capsules.