The University of Southampton
University of Southampton Institutional Repository

Study of direct gas injection into stagnation zone of blunt nose at hypersonic flow

Study of direct gas injection into stagnation zone of blunt nose at hypersonic flow
Study of direct gas injection into stagnation zone of blunt nose at hypersonic flow
Direct gas injection in the shocked or compressed region has importance in many applications from drag control to ignition and pressure gain combustion. This numerical study is focused on direct light gas injection into the stagnation zone of a blunt nose at hypersonic speed, aiming to achieve efficient active drag control. The direct injection of a inert gas helium and a reactive gas hydrogen in the stagnation zone of bow-shock, are compared numerically with the air injection at hypersonic flow Mach 6 with freestream conditions according to the Earth’s altitude of 10 km. The two-dimensional axisymmetric numerical simulations are performed by adaptive mesh refinement and solving compressible Euler equations for multiple thermally perfect species with a reactive source term using AMROC solver. The hydrogen combustionand ignition is modelled using one-step reaction mechanism. The pressure drag on the blunt nose has been compared for different injection pressure ratios for all three gas injections and it was concluded that the sonic injection (at Mach = 1) of light gases He and H2 provides similar performance in the pressure drag reduction up to 77%, as compared to air injection, with 62.5% and 73.5% lesser mass flow rate, respectively. In case of supersonic gas injection (at Mach = 2), the inert gas helium injection performs relatively better (up to 82% pressure drag reduction) or comparable to supersonic air injection for lesser mass flow rates. Various flow features in the short and long penetration modes of sonic and supersonic gas injections are also analyzed in the reactive and non-reactive flow-fields.
American Institute of Aeronautics and Astronautics
Harmon, Peter
7480fd91-21db-43a3-8f3c-c34b678ed1ea
Vashishtha, Ashish
c94f2d00-b34f-4abd-80a7-6346da51ebb8
Callaghan, Dean
bbb42ee3-fe01-4efc-94d5-21257be97c37
Nolan, Cathal
cccd2620-c956-4d33-b8e9-b19fa105a76b
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Harmon, Peter
7480fd91-21db-43a3-8f3c-c34b678ed1ea
Vashishtha, Ashish
c94f2d00-b34f-4abd-80a7-6346da51ebb8
Callaghan, Dean
bbb42ee3-fe01-4efc-94d5-21257be97c37
Nolan, Cathal
cccd2620-c956-4d33-b8e9-b19fa105a76b
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314

Harmon, Peter, Vashishtha, Ashish, Callaghan, Dean, Nolan, Cathal and Deiterding, Ralf (2021) Study of direct gas injection into stagnation zone of blunt nose at hypersonic flow. In AIAA Propulsion and Energy Forum and Exposition. American Institute of Aeronautics and Astronautics. 13 pp . (doi:10.2514/6.2021-3529).

Record type: Conference or Workshop Item (Paper)

Abstract

Direct gas injection in the shocked or compressed region has importance in many applications from drag control to ignition and pressure gain combustion. This numerical study is focused on direct light gas injection into the stagnation zone of a blunt nose at hypersonic speed, aiming to achieve efficient active drag control. The direct injection of a inert gas helium and a reactive gas hydrogen in the stagnation zone of bow-shock, are compared numerically with the air injection at hypersonic flow Mach 6 with freestream conditions according to the Earth’s altitude of 10 km. The two-dimensional axisymmetric numerical simulations are performed by adaptive mesh refinement and solving compressible Euler equations for multiple thermally perfect species with a reactive source term using AMROC solver. The hydrogen combustionand ignition is modelled using one-step reaction mechanism. The pressure drag on the blunt nose has been compared for different injection pressure ratios for all three gas injections and it was concluded that the sonic injection (at Mach = 1) of light gases He and H2 provides similar performance in the pressure drag reduction up to 77%, as compared to air injection, with 62.5% and 73.5% lesser mass flow rate, respectively. In case of supersonic gas injection (at Mach = 2), the inert gas helium injection performs relatively better (up to 82% pressure drag reduction) or comparable to supersonic air injection for lesser mass flow rates. Various flow features in the short and long penetration modes of sonic and supersonic gas injections are also analyzed in the reactive and non-reactive flow-fields.

Text
18_AIAA_PnE2021_Uploaded08072021 - Accepted Manuscript
Restricted to Repository staff only
Request a copy

More information

Accepted/In Press date: 8 July 2021
Published date: 28 July 2021

Identifiers

Local EPrints ID: 450354
URI: http://eprints.soton.ac.uk/id/eprint/450354
PURE UUID: 733e9a66-e744-4bb0-ab8e-363430f0bce0
ORCID for Ralf Deiterding: ORCID iD orcid.org/0000-0003-4776-8183

Catalogue record

Date deposited: 23 Jul 2021 18:13
Last modified: 17 Mar 2024 03:39

Export record

Altmetrics

Contributors

Author: Peter Harmon
Author: Ashish Vashishtha
Author: Dean Callaghan
Author: Cathal Nolan
Author: Ralf Deiterding ORCID iD

Download statistics

Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.

View more statistics

Atom RSS 1.0 RSS 2.0

Contact ePrints Soton: eprints@soton.ac.uk

ePrints Soton supports OAI 2.0 with a base URL of http://eprints.soton.ac.uk/cgi/oai2

This repository has been built using EPrints software, developed at the University of Southampton, but available to everyone to use.

We use cookies to ensure that we give you the best experience on our website. If you continue without changing your settings, we will assume that you are happy to receive cookies on the University of Southampton website.

×