Oblique Detonation Wave Control with O 3 and H 2 O 2 Sensitization in Hypersonic Flow

Ashish Vashishtha, Snehasish Panigrahy, Dino Campi, Dean Callaghan, Cathal Nolan and Ralf Deiterding
Additional contact information
Ashish Vashishtha: Department of Aerospace & Mechanical Engineering, South East Technological University (SETU), Carlow Campus, R93 V960 Carlow, Ireland
Snehasish Panigrahy: Department of Energy Science and Engineering, Indian Institute of Technology, Delhi 110016, India
Dino Campi: Department of Aerospace & Mechanical Engineering, South East Technological University (SETU), Carlow Campus, R93 V960 Carlow, Ireland
Dean Callaghan: The Center for Research and Enterprise in Engineering (engCORE), South East Technological University (SETU), Carlow Campus, R93 V960 Carlow, Ireland
Cathal Nolan: Department of Aerospace & Mechanical Engineering, South East Technological University (SETU), Carlow Campus, R93 V960 Carlow, Ireland
Ralf Deiterding: Aerodynamics and Flight Mechanics Research Group, University of Southampton, Boldrewood Innovation Campus, Southampton SO16 7QF, UK

Energies, 2022, vol. 15, issue 11, 1-17

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 2 O 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 2 O 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 2 O 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 2 O 2 and O 3 addition, respectively, during an abrupt OSW to ODW transition at Mach 7.

Keywords: schramjet; oblique detonation wave; hypersonic flow; detailed chemical kinetics; fuel-sensitization (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2022
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