In this study, an experimental study of the burning rate of solid fuel in a model solid
propellant rocket motor (SRM) E-5-0 was conducted using a non-invasive control method …

In each of the three different funding phases the program has been focused on different
aspects. While during the first phase main emphasis has been put explorative research …

Ludwieg 管风洞能低成本, 高效率地产生低湍流度的高超声速气流, 被广泛用于高超声速(马赫数
6 及以上) 基础空气动力学实验研究. 尽管Ludwieg 管式高超声速风洞逐渐普及 …

The turbulent wake of a generic space launcher wind tunnel model with an underexpanded
nozzle jet is investigated experimentally and numerically to gain insight into the variation of …

A strategy for scale-resolving simulations of bi-species turbulent flows is presented. It relies
on a combination of Zonal Detached Eddy Simulation (ZDES) and an original low …

In this work, the high-altitude environment simulation study was carried out at an altitude of
65 km exceeding Mach number of 6 after the launch of Korean Space Launch Vehicle using …

The effects of an exhaust plume and nozzle length on the flow organization of axisymmetric
base flows have been studied experimentally at Mach numbers of 0.76 and 2.2 using …

The influence on the turbulent wake of a generic space launcher model due to the presence
of an under-expanded jet is investigated experimentally. Wake flow phenomena represent a …

This paper considers the influence of Reynolds number on the transition behavior of a dual-
bell nozzle with special regard to hysteresis. For this purpose, Reynolds averaged Navier …

The typical afterbody flow of a space launcher is characterized by a strong interaction of the
engine's exhaust jet and the separated shear layer emerging from the main body. This …