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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 8, Issue 4 - Dec 2004
Volume 8, Issue 3 - Sep 2004
Volume 8, Issue 2 - Jun 2004
Volume 8, Issue 1 - Mar 2004
Selecting the target year
Preparation of Ultra Fine Ammonium Perchlorate Crystals
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 1~7
The precipitation of ultra fine ammonium perchlorate(UFAP) crystals from the N-methyl pyrrolidone(NMP) solutions of ammonium perchlorate(AP) was studied. The characteristics of the precipitated crystals were investigated by means of scanning electron micrograph(SEM), X-ray diffraction(XRD), and thermogravimetric analysis(TGA). When chloroform, methylene chloride and toluene were the precipitants, the product crystals had a mean particle size less than 2
. The crystallographical property and thermal decomposition behavior of the prepared UFAP were almost the same as those of the commercial AP.
Aerodynamic Characteristics of Supersonic Jets Impinging on
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 8~15
Supersonic jets impinging on
wedge were investigated to obtain fundamental design data for jet deflector It was of interest to study flow phenomena such as shock interaction and separation induced by shear layer. Experiments using supersonic cold flow system were conducted for Schlieren flow visualization and measurement of surface pressure. Numerical results were compared with the experimental results. The major parameters are underexpansion ratio, distance from nozzle to apex and design Mach number. Flow conditions were obtained for the wedge shock to attach on or detach from the wedge. The dominant feature of flow-field is shock pattern induced by the Interaction between the wedge shock and the barrel shock.
Application of Preconditioning to Navier-Stokes Equations
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 16~26
The objective of this study is to apply preconditioning to Wavier-Stokes equations with a turbulence model. The concept of a pseudo sonic speed was adopted. Roe's FDS was used for spatial discretization, LU-SGS scheme was used for time integration. In order to test the algorithms, the low speed flows around NACA airfoils and the flows through supersonic nozzle were calculated. The algorithm developed in the present study shows good performance in the calculations of low speed viscous flows and supersonics flows.
Convergence Characteristics of Preconditioned Euler Equations
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 27~37
The convergence characteristics of preconditioned Euler equations were studied. A perturbation analysis was conducted to understand the behavior of the preconditioned Euler equations. Various speed flows in a two-dimensional channel with a 10％ circular arc in the middle of the channel were calculated. Roe's FDS scheme was used for spatial discretization and the LU-SGS scheme was used for time integration. It is shown that the convergence characteristics of pressure and velocity were maintained regardless of the Mach numbers but that the convergence characteristics of temperature were strongly related to the Mach number and became worse as the Mach number decreased. The perturbation analysis well explained the trend of the convergence characteristics and showed that the convergence characteristics are strongly related with the behavior o( the Preconditioning matrix.
Combustion Characteristics of the Slinger Combustor
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 38~43
The study was performed to understand combustion characteristics of the slinger combustor. Liquid fuel is discharged radially outwards through injection holes drilled in the high speed rotating shaft. The spray test was peformed to verify atomizing characteristics with variation of fuel nozzle rotational speed by using PDPA system. SMD was measured at different RPM and values are 70
at 5,000RPM rpm, 60
at 10,000RPM and 40
at 20,000RPM. In the results, we found out that SMD is grown smaller with increasing rotational speed. In KARI combustion test facility, Ignition and combustion tests were performed by using combustor test rig. In the test results, ignition and combustion efficiency were improved according to increasing rotational speed. The measured radial temperature distribution at the combustor exit shows stable and fairly good distribution.
Effects of Aspect Ratio of a Fuel Injection Nozzle into a Supersonic Air Stream on Combustion Characteristics
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 44~53
This paper is to investigate the combustion characteristics with a three dimensional chemical reacting flow on the aspect ratio of an exit configuration of the slit type nozzle for the fuel injection and to device the methods of combustion／mixing enhancement. The results show that both inside inflow and slit side vertices should be considered from a viewpoint of the mixing. The combustion efficiency becomes the smallest at aspect ratio, where the aspect ratio is less and more than unity, respectively. The total pressure loss becomes the largest at aspect ratio of unity due to the high penetration. All results imply that a streamwise very long slit is desirable with respect to the combustion and the pressure loss.
Combustion Characteristics of Double Swirl Coaxial Injector in High Pressure Thrust Chamber
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 54~60
Experimental study on combustion characteristics of double swirl coaxial injectors has been conducted for the assessment of critical injector design parameters. A reusable, subscale thrust chamber has been fabricated with a water-cooled copper nozzle. Two different configurations of injectors have been tested for the understanding of the effects of recess length on high pressure combustion. Clearly, the recess length drastically affects the combustion efficiency and hydraulic characteristics of an injector. Internal mixing of propellants in an injector with recess number of two increases a combustion efficiency and reveals sound combustion although a pressure drop required for the same amount of mass flow rates increases compared with an injector of recess number of one.
Combustion Characteristics of Hypersonic SCRamjet Engine
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 61~69
This paper describes numerical efforts to characterize the flame-holding and air-fuel mixing process of model SCRamjet engine combustor, where a hydrogen jet injected into a supersonic cross flow and in a cavity Combustion phenomena in a model SCRamjet engine, which has been experimentally studied at University of Queensland and Australian National University using a free-piston shock tunnel, was observed around separation region of upstream of the normal injector and inside of cavity. The results show that the separation region and cavity generates several recirculation zones, which increase the fuel-air mixing. Self ignition occurs in the separation-freestream and cavity-freestream interface.
Aerodynamic and Structural Design on Small Wind Turbine Blade Using High Performance Configuration and E-Glass/Epoxy-Urethane Foam Sandwich Composite Structure
Chang-Duk Kong ; Jo-Hyug Bang ;
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 70~80
This study proposes a development result for the 1-kW class small wind turbine system, which is applicable to relatively low wind speed regions like Korea and has the variable pitch control mechanism. In the aerodynamic design of the wind turbine blade, parametric studies were carried out to determine an optimum aerodynamic configuration which is not only more efficient at low wind speed but whose diameter is not much larger than similar class other blades. A light composite structure, which can endure effectively various loads, was newly designed. In order to evaluate the structural design of the composite blade, the structural analysis was peformed by the finite element method. Moreover both structural safety and stability were verified through the full- scale structural test.
Heat Flux Evaluation of KSR-III Sub-scale Chamber
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 81~84
A water-cooled calorimeter chamber with 8 cooling channels based on KSR-III sub-scale chamber has been designed and manufactured. One dimensional empirical correlation has been used at the design stage and full three-dimensional CFD analysis has been conducted to confirm the cooling condition for hot fire test is safe. Predicted heat flux is accurate around the nozzle throat when the thermal resistance of carbon deposit is considered. However relatively large difference is observed in chamber part.
Development Trends of Combustor Technology for Jet Engines
Journal of the Korean Society of Propulsion Engineers, volume 8, issue 1, 2004, Pages 85~97
The advanced technology of jet engine combustor such as high temperature composite materials is being developed to enhance the life of turbine and to minimize pollutants emission in foreign countries. The domestic development status of combustor for jet engine are only limited to the basic technology of small engine combustor. The development program of combustor are required to improve current technology.