Aerodynamics of ducted re-entry vehicles

Raj, C. Anbu Serene; Narasimhavaradhan, M.; Vaishnavi, N.; Arunvinthan, S.; Arjani, A. Al; Pillai, S. Nadaraja

doi:10.1016/j.cja.2020.02.019

Cited by 16 publications

(9 citation statements)

References 20 publications

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“…Then, any medium leakage laws linking the pressure drop at the permeable boundary with the parameters of the oncoming flow become unsuitable in principle. There is thus a need to develop new experimental ways of determining the boundary relations [20][21][22].…”

Section: Introductionmentioning

confidence: 99%

Prototyping and Study of Mesh Turbomachinery Based on the Euler Turbine

et al. 2021

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This paper presents a scientific development aimed at improving the efficiency of turbomachines through the joint use of rotary-vane and vortex workflows. In the well-known Euler turbine, the rotor flow channels represent a set of curved pipes. The authors propose to consider in more detail the possibilities of using such rotating pipes in the implementation of an ejection (vortex) workflow. A hybrid pump was considered with the conclusion that its workflow can be described using two Euler equations. The results of computer simulation indicate that hybrid turbomachines are promising. The use of additive technology allowed the creation of micromodels of the Euler turbine with various rotor designs. Laboratory hydraulic tests showed that the liquid inlet to the rotor is possible in pulse mode. Laboratory tests of micromodels using compressed air showed that gas (or liquid) motion through curved pipes could be carried out from the rotor periphery to its center and then back, albeit through another curved pipe. The research results demonstrated that the scientific and technical potential of the Euler turbine is not yet fully unlocked, and research in this direction should continue. The study results are applicable in various industries including the energyeconomy, robotics, aviation, and water transport industries.

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Section: Introductionmentioning

confidence: 99%

Prototyping and Study of Mesh Turbomachinery Based on the Euler Turbine

et al. 2021

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“…Aerospace 2024, 11, x FOR PEER REVIEW 5 of 21 limitations, the suspension lines were neglected. The boundary conditions [18] are summarized in Table 1. The time step is 1.0 × 10 −4 s and the overall runtime of numerical simulations conducted is 0.126 s.…”

Section: Grid-independence Analysismentioning

confidence: 99%

Large-Eddy Simulations of a Hypersonic Re-Entry Capsule Coupled with the Supersonic Disk-Gap-Band Parachute

Peri,

Ingenito,

Teofilatto

2024

Aerospace

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The goal of this paper is to investigate the aerodynamic and aerothermodynamic behavior of the Schiaparelli capsule after the deployment of a supersonic disk-gap-band (DGB) parachute during its re-entry phase into the Martian atmosphere. The novelty of this work lies in the investigation by LES (large-eddy simulations) of the coupled interaction of the flow field generated behind the capsule and that in front of the flexible DGB parachute. These simulations are performed at an altitude of 10 km and a Mach number around 2, i.e., a regime in which large canopy-area oscillations are observed. LES results have shown a strong interaction between the bow shock, the recompression and expansion waves, high pressure, density and temperature gradients, heat flux towards the airstream and the body implying turbulence generation, ingestion, and amplification through the shock waves. Vortices released from the capsule at a frequency of about 52 Hz and 159 Hz, corresponding to Strouhal numbers of ~0.2 and 0.75, respectively, are the main factors responsible for the instabilities of the hypersonic re-entry capsule and the disk-gap-band parachute coupled system. The nonlinear turbulence flow field generated at the capsule back is amplified when passing the parachute bow shock, and this is responsible for the non-axisymmetric behavior around and behind the parachute that caused the uncontrolled capsule oscillations and the Schiaparelli mission failure. In fact, an LES of the parachute without the capsule, for the same conditions, show a completely axisymmetric field, varying in time, but axisymmetric. In order to avoid this turbulence amplification, dampening of the vortex shedding is critical. Different techniques have been already proposed for other applications. In the case of capsule re-entry, due to the high temperatures in front of the capsule behind the bow shock since air plasma is generated, damping of the vortex shedding could be achieved by means of magnetohydrodynamic (MHD) control.

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“…In this case, the parameters on the windward side of the permeable body boundary cease to depend on the conditions on its leeward side. Then, any medium leakage laws linking the pressure drop at the permeable boundary with the parameters of the oncoming flow become unsuitable in principle, and there is a need to develop new experimental ways of determining the boundary relations [43][44][45].…”

Section: -2-strengths and Limitationsmentioning

confidence: 99%

Development and Prototyping of Jet Systems for Advanced Turbomachinery with Mesh Rotor

et al. 2021

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This article presents the research results that aim to develop promising mesh turbomachines equipped with jet control systems. The turbomachines operating in difficult conditions in oil and gas production are mainly considered. At the same time, some research results can be used in other production branches, including power engineering and transport. Three-dimensional models for computer simulation of net turbines and jet control systems were developed. Prototypes and micromodels were created to test the performance of mesh turbines and jet control systems using additive technologies. A methodological approach is proposed to create a classification of jet control systems considering their design and technological features. In the course of numerical experiments, the extreme conditions of fluid and gas outflow through a nozzle equipped with a velocity vector control system, in the control range of adjustment of the velocity vector deflection angle from + 90o to -90o within a geometric hemisphere, have been considered for the first time. It was also shown that when using a dual-channel nozzle, there are possibilities to adjust the velocity vector angle (thrust vector) in the range of + 180o to -180owithin the geometric sphere. Compared with the known variants, the control range of the velocity vector angle is increased by nine times. These calculated data are presented in addition to the previously published results of physical laboratory experiments. Preliminary results of numerical experiments show the possibility of creating a new theory in the field of mesh turbines and jet systems. Patents support the novelty of the developed technical solutions. Doi: 10.28991/esj-2021-01311 Full Text: PDF

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Aerodynamics of ducted re-entry vehicles

Cited by 16 publications

References 20 publications

Prototyping and Study of Mesh Turbomachinery Based on the Euler Turbine

Prototyping and Study of Mesh Turbomachinery Based on the Euler Turbine

Large-Eddy Simulations of a Hypersonic Re-Entry Capsule Coupled with the Supersonic Disk-Gap-Band Parachute

Development and Prototyping of Jet Systems for Advanced Turbomachinery with Mesh Rotor

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