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Oblique detonation wave control with O3 and H2O2 sensitization in hypersonic flow

Oblique detonation wave control with O3 and H2O2 sensitization in hypersonic flow
Oblique detonation wave control with O3 and H2O2 sensitization in hypersonic flow
This numerical study investigates the effects of adding a small amount of ignition promoters for controlling the wedge induced oblique shock wave (OSW) to oblique detonation wave (ODW) transition in a premixed hydrogen air mixture at hypersonic speeds. The time dependent two-dimensional compressible Euler equations for multiple thermally perfect species with a reactive source term are solved using adaptive mesh refinement and detailed chemical kinetics. The wedge with a fixed angle 26◦ exhibits abrupt to smooth transitions for freestream Mach numbers 7 - 9 (speeds 2.8 -3.2 km/s) at a pressure of 20 kPa and temperature of 300K. The small amount (1000 PPM by vol.) of H2O2 and O3 is found to be effective in significantly reducing the initiation length for oblique detonation transition for all the Mach numbers, which suggests a practical approach to increase the operating flight range for oblique detonation wave engine with a finite length wedge. At Mach number 8, the abrupt OSW to ODW transition turns towards smooth transition with a small amount of H2O2 and O3 addition. Comparatively, O3 addition was found effective in reducing the ODW initiation length by promoting reactivity behind even a weaker oblique shock at low Mach number 7 for abrupt transition, while H2O2 addition was more effective than O3 at high Mach numbers 8 and 9 during smooth transition. The maximum 73 % and 80 % reduction in initiation length of ODW was observed with 10000 PPM H2O2 and O3 addition, respectively, during abrupt OSW to ODW transition at Mach 7.
Schramjet, Oblique Detonation Wave, Hypersonic Flow, Detailed Chemical Kinetics, Fuel-sensitization
1996-1073
Vashishtha, Ashish
1fe96160-921d-40ac-8dcf-e4a7d9612129
Panigrahy, Snehasish
b42c7fdd-50d4-4275-9b91-a9c5ef537a85
Campi, Dino
41034a6e-6686-4c72-a6a4-8092dc88b3d9
Callaghan, Dean
bbb42ee3-fe01-4efc-94d5-21257be97c37
Nolan, Cathal
cccd2620-c956-4d33-b8e9-b19fa105a76b
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Vashishtha, Ashish
1fe96160-921d-40ac-8dcf-e4a7d9612129
Panigrahy, Snehasish
b42c7fdd-50d4-4275-9b91-a9c5ef537a85
Campi, Dino
41034a6e-6686-4c72-a6a4-8092dc88b3d9
Callaghan, Dean
bbb42ee3-fe01-4efc-94d5-21257be97c37
Nolan, Cathal
cccd2620-c956-4d33-b8e9-b19fa105a76b
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314

Vashishtha, Ashish, Panigrahy, Snehasish, Campi, Dino, Callaghan, Dean, Nolan, Cathal and Deiterding, Ralf (2022) Oblique detonation wave control with O3 and H2O2 sensitization in hypersonic flow. Energies, 15 (11), [4140]. (doi:10.3390/en15114140).

Record type: Article

Abstract

This numerical study investigates the effects of adding a small amount of ignition promoters for controlling the wedge induced oblique shock wave (OSW) to oblique detonation wave (ODW) transition in a premixed hydrogen air mixture at hypersonic speeds. The time dependent two-dimensional compressible Euler equations for multiple thermally perfect species with a reactive source term are solved using adaptive mesh refinement and detailed chemical kinetics. The wedge with a fixed angle 26◦ exhibits abrupt to smooth transitions for freestream Mach numbers 7 - 9 (speeds 2.8 -3.2 km/s) at a pressure of 20 kPa and temperature of 300K. The small amount (1000 PPM by vol.) of H2O2 and O3 is found to be effective in significantly reducing the initiation length for oblique detonation transition for all the Mach numbers, which suggests a practical approach to increase the operating flight range for oblique detonation wave engine with a finite length wedge. At Mach number 8, the abrupt OSW to ODW transition turns towards smooth transition with a small amount of H2O2 and O3 addition. Comparatively, O3 addition was found effective in reducing the ODW initiation length by promoting reactivity behind even a weaker oblique shock at low Mach number 7 for abrupt transition, while H2O2 addition was more effective than O3 at high Mach numbers 8 and 9 during smooth transition. The maximum 73 % and 80 % reduction in initiation length of ODW was observed with 10000 PPM H2O2 and O3 addition, respectively, during abrupt OSW to ODW transition at Mach 7.

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More information

Accepted/In Press date: 1 June 2022
Published date: 4 June 2022
Keywords: Schramjet, Oblique Detonation Wave, Hypersonic Flow, Detailed Chemical Kinetics, Fuel-sensitization

Identifiers

Local EPrints ID: 458009
URI: http://eprints.soton.ac.uk/id/eprint/458009
ISSN: 1996-1073
PURE UUID: f999cf08-d6a7-4b2a-b9eb-5b5b8324dcac
ORCID for Ralf Deiterding: ORCID iD orcid.org/0000-0003-4776-8183

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Date deposited: 24 Jun 2022 17:33
Last modified: 25 Jun 2022 01:48

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Contributors

Author: Ashish Vashishtha
Author: Snehasish Panigrahy
Author: Dino Campi
Author: Dean Callaghan
Author: Cathal Nolan
Author: Ralf Deiterding ORCID iD

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