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 of 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 a temperature of 300 K. The small amount (1000 PPM by vol.) of H
2O
2 and O
3 is found to be effective at significantly reducing the initiation length for the oblique detonation transition for all 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 a smooth transition with a small amount of H
2O
2 and O
3 addition. Comparatively, O
3 addition was found to be 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 H
2O
2 addition was more effective than O
3 at high Mach numbers 8 and 9, during a smooth transition. The maximum 73% and 80% reduction in initiation length of ODW was observed with 10,000 PPM H
2O
2 and O
3 addition, respectively, during an abrupt OSW to ODW transition at Mach 7.
detailed chemical kinetics, fuel-sensitization, hypersonic flow, oblique detonation wave, schramjet
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
1 June 2022
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).
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 of 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 a temperature of 300 K. The small amount (1000 PPM by vol.) of H
2O
2 and O
3 is found to be effective at significantly reducing the initiation length for the oblique detonation transition for all 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 a smooth transition with a small amount of H
2O
2 and O
3 addition. Comparatively, O
3 addition was found to be 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 H
2O
2 addition was more effective than O
3 at high Mach numbers 8 and 9, during a smooth transition. The maximum 73% and 80% reduction in initiation length of ODW was observed with 10,000 PPM H
2O
2 and O
3 addition, respectively, during an abrupt OSW to ODW transition at Mach 7.
Text
11c_MDPI_Energies_RV1
- Accepted Manuscript
Text
energies-15-04140-v2
- Version of Record
More information
Accepted/In Press date: 1 June 2022
Published date: 1 June 2022
Additional Information:
Funding Information:
The authors would like to acknowledge the Irish Centre for High-End Computing (ICHEC) for the provision of computing resources for this study.
Publisher Copyright:
© 2022 by the authors. Licensee MDPI, Basel, Switzerland.
Keywords:
detailed chemical kinetics, fuel-sensitization, hypersonic flow, oblique detonation wave, schramjet
Identifiers
Local EPrints ID: 458009
URI: http://eprints.soton.ac.uk/id/eprint/458009
ISSN: 1996-1073
PURE UUID: f999cf08-d6a7-4b2a-b9eb-5b5b8324dcac
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Date deposited: 24 Jun 2022 17:33
Last modified: 17 Mar 2024 03:39
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Contributors
Author:
Ashish Vashishtha
Author:
Snehasish Panigrahy
Author:
Dino Campi
Author:
Dean Callaghan
Author:
Cathal Nolan
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