Simulation of conical oblique detonation waves in hypersonic flow of hydrogen-air.

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  • English
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Oblique Detonation Wave (ODW) is a key component for hypersonic combustion engines. Its understanding is essential for designing combustors but reliable information on combustion process and exact ODW structure are difficult to obtain. Axisymmetric sharp cones can produce the purest two-dimensional ODW. This study simulates conical ODWs with hypersonic inflow of stoichiometric H2-air at Mach 7.36, using axisymmetric multi-species Laminar Navier-Stokes equations with the Jachimowski and Lutz combustion models. Numerical solutions of inviscid flow, at 40°, 35° and 32° cones, show steady-state overdriven ODW ignited by the pressure coupling of a shock wave and deflagration waves. At 30.5° and 30° cones, the ODWs are near the Chapman-Jouguet (CJ) condition and the coupling occurs between the shock wave and an internal post-shock ODW. The predicted CJ condition is between 30° and 29.5°, with constant detonation angle and minimum entropy being 42.3° and 1864 JkgK . The induction distance is the most sensitive parameter.

The Physical Object
Pagination95 leaves.
ID Numbers
Open LibraryOL19214539M
ISBN 100494021381

Initiation structure of oblique detonation waves behind conical shocks. The understanding of oblique detonation dynamics has both inherent basic research value for high-speed compressible reacting flow and propulsion application in hypersonic aerospace by: In recent years, high efficiency propulsion systems have generated great interest for their use in the development of air-breathing hypersonic aircrafts.

The concept of oblique detonation waves has led to the development of Oblique Detonation Wave Engines (ODWE) [. 1] and Ram Accelerators [2]. Abstract. We studied the oblique detonation waves around hypersonic projectiles.

Projectiles (10 mm diameter, conical nose shape) were fired at hypersonic speeds ( ± km/s) into stoichiometric hydrogen-oxygen mixtures (pressure between 10 kPa and Cited by: 4.

The numerical simulation of supersonic flow over a cone is carried out to investigate oblique detonation waves. A three-dimensional (3D) conical oblique detonation wave is. Numerical study of oblique detonation wave initiation in a stoichiometric hydrogen-air mixture 17 September | Physics of Fluids, Vol.

27, No. 9 Analytical and Numerical Investigations of Wedge-Induced Oblique Detonation Waves at Low Inflow Mach NumberCited by: Shcramjet combustion is based on oblique detonation wave processes.

As such an in-depth understanding of the physics of these processes is important to shcramjet design. Oblique detonation wave (ODW) stabilized over a body was given interests for a last decade, since is it considered as a promising combustion mechanism for novel hypersonic propulsion systems such as a ram accelerator or an oblique detonation wave engine.

Description Simulation of conical oblique detonation waves in hypersonic flow of hydrogen-air. EPUB

Pratt[1] et al. summarized the classical theory. Initiation structure of oblique detonation waves behind conical shocks Physics of Fluids, Vol. 29, No. 8 Wedge-stabilized oblique detonation in an inhomogeneous hydrogen Cited by:   Initiation Simulation of conical oblique detonation waves in hypersonic flow of hydrogen-air.

book of wedge-induced oblique detonation waves in a stoichiometric hydrogen-air mixture Proceedings of the Combustion Institute, Vol. 36, No. 2 Numerical study of oblique detonation wave initiation in a stoichiometric hydrogen-air mixtureCited by:   Three dimensional structure of stabilization of oblique detonation wave in a hypersonic flow.

Proc. Combust. Inst. 27, – () CrossRef Google ScholarAuthor: Jeong-Yeol Choi, In-Seuck Jeung. Oblique detonation waves (ODWs) have been studied widely as the basis of detonation-based hypersonic engines, but there are few studies on ODWs in a confined space.

This study simulates ODW reflection on a solid wall before an outward turning corner for a simplified combustor–nozzle flow based on a two-step kinetic model. Wedge-Stabilized Oblique Detonation Waves in a Hypersonic Hydrogen-Air Premixed Freestream. Three-dimensional structure of stabilization of oblique detonation wave in hypersonic flow.

Symposium (International) on Combustion, Vol. 27, No. 2 Numerical modeling of standing oblique detonation by:   Two-dimensional, oblique detonations induced by a wedge are simulated using the reactive Euler equations with a detailed chemical reaction model.

The focus of this study is on the oblique shock-to-detonation transition in a stoichiometric hydrogen-air mixture.

A combustible, gas mixture at low pressure and high temperature, corresponding to the realistic, inflow conditions applied in oblique Cited by: Visualization of the non-steady state oblique detonation wave phenomena around hypersonic spherical projectile Proceedings of the Combustion Institute, Vol.

33, No. 2 Combustion wave propagation and detonation initiation in the vicinity of closed-tube end wallsCited by: An oblique detonation wave for a Mach 7 inlet flow over a long enough wedge of 30° turning angle is simulated numerically using Euler equation and one-step rection model.

A numerical study was performed to investigate the detailed effects of activation energy E a on the oblique detonation wave surface instability. Numerical simulations were performed using an ideal reactive flow model given by the inviscid Euler equations with one-step irreversible Arrhenius reaction by: 8.

Formation of transverse waves in oblique detonations. The structure of oblique detonation waves stabilized on a hypersonic wedge in mixtures characterized by a large activation energy is investigated via steady method of characteristics (MoC) calculations and unsteady computational flowfield simulations.

The second model in our investigation is a 25°/55° cone/cone configuration with a sharp leading edge.

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The free stream conditions of this computation are U ∞ = m/s, T ∞ = K, P ∞ = Pa and ρ ∞ = × Kg/m corresponding Mach number is and the Reynolds number based on the length of the first cone is ×10 wall temperature also remains constant.

This method of simulating oblique detonations in hypersonic flow involved the periodic initiation of multiple cylindrical detonation fronts, which upon interaction quickly transitioned to an oblique detonation wave.

Its axisymmetric analog was the point ignition of multiple spherical detonation waves forming a conical oblique : Baki M. Cetegen, Lynwood F. Crary, Eli K.

Dabora. We studied experimentally the shock waves and combustion waves generated by a hypersonic spherical projectile in an explosive mixture. An acetylene/oxygen mixture diluted with argon (2C 2 H 2 + 5O 2 + 7Ar) was used with various initial pressures (detonation cell sizes) to observe optically with a shadowgraph imaging system a shock-induced combustion (SIC), a stable oblique detonation wave Cited by:   Teng, Honghui Zhang, Yining and Jiang, Zonglin Numerical investigation on the induction zone structure of the oblique detonation ers & Fluids, Vol Cited by: 1.

Introduction. Oblique detonation wave (ODW) is a kind of supersonic combustion formed when a detonable mixture flows onto a solid body at a speed exceeding its Chapman–Jouguet (C–J) speed.It has been studied extensively as a potential power source for conceptual hypersonic propulsion technologies such as an Oblique Detonation Wave Engine (ODWE) and a Ram Accelerator Cited by: Two-dimensional, oblique detonation waves (ODWs) in a stoichiometric hydrogen-air mixture are simulated with the reactive Euler equations using a detailed chemical reaction model.

This study focuses on blunt wedge induced ODWs, which are not only influenced by inflow parameters but also the size of Cited by: 1.

Hypersonic Flow is the ideal text/reference for students and professionals interested in this burgeoning field. Written by a nationally recognized authority on the subject, it features a clear, accessible writing style along with sufficient depth and detail for self-study, First published: Sep, The Oblique Detonation Wave Engine is among the promising choices for hypersonic propulsion systems.

It is of great importance to investigate the init. The stabilization effect of porous coating on the hypersonic boundary layers over flat plates and cones has been studied by theoretical analyses, experiments, and numerical simulations. It was found that porous coating slightly destabilizes Mack's first mode whereas it significantly stabilizes Mack's second by: Abstract.

The prompt oblique detonation waves (ODWs) induced by finite-length wedges are investigated by numerical simulations.

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The numerical results show that premature ignition resulting from the initial conditions can result in the formation of the prompt ODWs that cannot take place spontaneously over the : Yan Liu, Jianping Wang.

Simulation of hypersonic speed (Mach 5) In aerodynamics, a hypersonic speed is one that greatly exceeds the speed of sound, often stated as starting at speeds of Mach 5 and above. [1]. Introduction to Hypersonic Flow has been made available to the English speaking reader because of its usefulness for those individuals desirous of obtaining an introduction to the subject.

Written by an internationally acknowledged expert in the field of hypersonic flow, the book makes available heretofore unpublished Soviet work, as well as Book Edition: 1. Sabet, A. I., “Investigation of Equilibrium and Chemical Kinetic Behaviour of Detonation Waves in Hydrogen-Air Mixtures and an Evaluation of the Oblique Detonation Wave as the Combustor for a Scramjet”, Masters Thesis, Rensselaer Polytechnic Institute, Troy, New York.

Google ScholarCited by:. For CFD validation, hypersonic flow fields are simulated and compared with experimental data specifically designed to recreate conditions found by hypersonic vehicles. Simulated flow fields on a cone-ogive with flare at Mach are compared with experimental data from NASA Ames Research Center ” hypersonic wind tunnel.

Abstract. A computational study of wedge-induced oblique shock and detonation wave phenomena in the flow of a combustible mixture over a wedged channel is presented with the purpose of understanding the fundamental gasdynamics of the waves and their by: Recompression of nonequilibrium flow in the wake of a blunted cone.

Flow in the TCM2-Marseille hypersonic facility: some new experimental results Experimental reconsideration of the state of the art of oblique shock-wave reflections in steady flows.

Large-scale confined hydrogen-air detonation experiments and their numerical simulation.