Simulation of Conical Oblique Detonation Waves in Hypersonic Flow of H↓2-air [microform] PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Simulation of Conical Oblique Detonation Waves in Hypersonic Flow of H↓2-air [microform] PDF full book. Access full book title Simulation of Conical Oblique Detonation Waves in Hypersonic Flow of H↓2-air [microform] by Felisa Yue Zhang. Download full books in PDF and EPUB format.
![Simulation of Conical Oblique Detonation Waves in Hypersonic Flow of H↓2-air [microform] PDF](https://books.google.com/books/content/images/frontcover/VxCJtgAACAAJ?fife=w150-h200)
Author: Felisa Yue Zhang
Publisher: Library and Archives Canada = Bibliothèque et Archives Canada
ISBN: 9780494021385
Category : Airplanes
Languages : en
Pages : 190
Get Book Here
Book Description
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.
![Simulation of Conical Oblique Detonation Waves in Hypersonic Flow of H↓2-air [microform] PDF](https://books.google.com/books/content/images/frontcover/VxCJtgAACAAJ?fife=w80-h100)
Author: Felisa Yue Zhang
Publisher: Library and Archives Canada = Bibliothèque et Archives Canada
ISBN: 9780494021385
Category : Airplanes
Languages : en
Pages : 190
Get Book Here
Book Description
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.
Author: Shaye Yungster
Publisher:
ISBN:
Category : Chemical reaction, Conditions and laws of
Languages : en
Pages : 24
Get Book Here
Book Description
Author: Shannon A. Grady
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Chen Chuck
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Daniel Alexander Rosato
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Get Book Here
Book Description
Detonation-based propulsion systems are desired due to their potential for thermodynamic cycle efficiencies much higher than traditional, constant pressure deflagration-based systems. Additionally, the ability to propagate in high-Mach number flow regimes makes detonations promising for supersonic combustion applications. Oblique detonation waves (ODW) are a subset of detonations that have been proposed for use in a number of detonation-based propulsion concepts. However, most studies into initiation and stabilization of ODWs have been numerical studies without sufficient experimental validation. Experimental setups, such as expansion tubes, typically have extremely limited run times ( 100 ms) due to practical difficulties in attaining the necessary conditions in a continuous flow ( 1 second) system. Those difficulties include the need for high pressures, temperatures, and the correct chemical composition in order to create a supersonic flow that is favorable for detonations. The work described within this dissertation focuses on the facility design and investigations into supersonic combustion and detonation stabilization using continuous flow facilities, including the HyperReact Facility. Using HyperReact, tests were conducted with varied pressures, temperatures, geometries, and flow compositions. From those tests, the operability map of the system was created, from which 3 major reaction regimes were defined. Those regimes include: intermittent, low-intensity reactions (regime I), intermittent, higher-intensity reactions (regime II), and quasi-stable reactions (regime III). Multiple diagnostics were performed, including high-speed shadowgraph and chemiluminescence imaging, Raman spectroscopy, as well as pressure and temperature measurements at multiple locations.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723048074
Category :
Languages : en
Pages : 152
Get Book Here
Book Description
The work performed by D. W. Bogdanoff and J.-L. Cambier during the period of 1 Feb. - 31 Oct. 1992 is presented. The following topics are discussed: (1) improvement in the operation of the facility; (2) the wedge model; (3) calibration of the new test section; (4) combustor model; (5) hydrogen fuel system for combustor model; (6) three inch calibration/development tunnel; (7) shock tunnel unsteady flow; (8) pulse detonation wave engine; (9) DCAF flow simulation; (10) high temperature shock layer simulation; and (11) the one dimensional Godunov CFD code. Heinemann, K. and Bogdanoff, David W. and Cambier, Jean-Luc Unspecified Center AERODYNAMICS; COMBUSTION CHAMBERS; COMPUTATIONAL FLUID DYNAMICS; DETONATION WAVES; HYDROGEN FUELS; HYPERSONIC SPEED; SHOCK LAYERS; SHOCK TUNNELS; UNSTEADY FLOW; CALIBRATING; COMPUTERIZED SIMULATION; FUEL SYSTEMS; HIGH TEMPERATURE; TEST CHAMBERS; WEDGES...
Author: Peter Ess
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Sandra Anderson Ashford
Publisher:
ISBN:
Category : Detonation waves
Languages : en
Pages : 488
Get Book Here
Book Description
Author: Kazuyoshi Takayama
Publisher: Springer
ISBN: 9783642468780
Category : Science
Languages : en
Pages : 0
Get Book Here
Book Description
Ram accelerators are among the most advanced tools for generating fluid dynamcis data in supersonic reacting systems. They require the combined action of combustion, wave systems and turbulence and are still a serious challenge for physicists and engineers. This book will serve as an introductionary textbook on ram accelerators and gives a thorough overview on research activities, performance modeling and high-pressure detonation dynamics.
Author: Naminosuke Kubota
Publisher: John Wiley & Sons
ISBN: 3527693513
Category : Science
Languages : en
Pages : 560
Get Book Here
Book Description
This third edition of the classic on the thermochemical aspects of the combustion of propellants and explosives is completely revised and updated and now includes a section on green propellants and offers an up-to-date view of the thermochemical aspects of combustion and corresponding applications. Clearly structured, the first half of the book presents an introduction to pyrodynamics, describing fundamental aspects of the combustion of energetic materials, while the second part highlights applications of energetic materials, such as propellants, explosives and pyrolants, with a focus on the phenomena occurring in rocket motors. Finally, an appendix gives a brief overview of the fundamentals of aerodynamics and heat transfer, which is a prerequisite for the study of pyrodynamics. A detailed reference for readers interested in rocketry or explosives technology.
