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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 6, Issue 4 - Dec 2002
Volume 6, Issue 3 - Sep 2002
Volume 6, Issue 2 - Jun 2002
Volume 6, Issue 1 - Mar 2002
Selecting the target year
A Study on the Calculation of Turbofan Engine Installed Performance for a Supersonic Aircraft
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 1~7
During the preliminary design phase of aircraft development, it is necessary to evaluate many potential engine/airframe combinations to determine the best solution to given set of mission requirements and it is very important to establish a methodology to calculate precisely engine installed performance. It was carried out to calculate turbofan engine installed performance of a supersonic aircraft for a given engine/aircraft configuration. Thus "Thrust minus drag accounting system" was introduced to identify and calculate the elements of installed thrust or installed propulsive force by using the database based on wind tunnel test data. This paper describes the calculated results of installed thrust of turbofan engine for a supersonic aircraft. aircraft.
The Study on Solid Propellant Deflagrabillity by Shotgun & RQ Bomb Test
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 9~17
This Study is to investigate 8 composite propellants including Butacene and
by Shotgun/RQ Bomb test. Burning rate and mechanical properity are known to be major factors in determining the deflagrability of propellant. Propellant including over 5.5% Butacene(Ferrocene grafted HTPB) burned out over 135 m/s of impact velocity during Shotgun/RQ Bomb test. It was blown that Butacene was very sensitive material under high velocity impact. In the test results, propellants under 25mm/s in burning rate at 1500 psia could meet the requirements for IM of UN Test Series 7c(ii). Propellant deflagrabillity depends on burning rate at performance in the results of the present.
A Study on the Cyclogram for the Firing Test of KSR-III Liquid Rocket Engine
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 19~27
The sequence of the propellant supply for ignition of a liquid rocket engine combustor is very important in the reliable and safe operation of the engine. The ignition sequence of KSR-III main engine was briefly described and the measuring parameters and their reliability determining ignition sequence were examined in this paper. The filling time of the engine propellant manifolds and the valve open/close time were reviewed to obtain the exact and reliable time of the propellant supply to the combustor. The combustion characteristics of the engine at starting were discussed at different supply lead of propellant. Finally, the hot firing test results with cyclogram determined by measuring parameters were presented.
Numerical Study for 3D Turbulent Flow in High Incidence Compressor Cascade
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 29~36
A numerical analysis based on two-dimensional and three-dimensional incompressible Wavier-Stokes equations has been carried out for double-circular-arc compressor cascades and the results are compared with available experimental data at various incidence angles. The 2-D and 3-D computational codes based on SIMPLE algorithm adopt pressure weighted interpolation method for non-staggered grid and hybrid scheme for the convective terms. Turbulence modeling is very important for prediction of cascade flows, which are extremely complex with separation and reattachment by adverse pressure gradient. Considering computation times,
turbulence model with wall function is used.
A Comparative Study on the Convective Heat Transfer Measurement Technique based on Liquid Crystal
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 37~43
There have been numerous experimental studies for heat transfer measurement technique. This study investigates optical methods for measuring local heat transfer coefficient using thermochromic liquid crystal. Transient and steady methods have been utilized to measure local heat transfer coefficient on a cylinder with a cross flow. The steady method is based on the heat-coating technique and two transient methods adopt by-pass technique and insertion technique, respectively. Both techniques of transient method employ heating technique in which the flow is heated by using the electric heater and cooling technique which cools the preheated cylinder. Experimental results indicate that each methods have nearly similar results. Detailed discussions have been made for its own advantages and disadvantages.
Pogo Analysis on the KSR-III Propulsion Feeding System
;;O. M. Menshikova;;;;;
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 45~52
This article deals with the introduction of longitudinal instability of liquid rocket (pogo) and the analytical results on the frequency responses of Korean Sounding Rocket (KSR-III) propulsion feeding system. Both the stiffness of bellows and the cavitation volume of venturi affect the frequency response of the feeding system. Especially, bellows has a great roll to reduce the natural frequency of the feeding system. Also, oxidizer and fuel feeding systems of the KSR-III have natural frequencies of about 280Hz and 90Hz, respectively.
Effect of acoustic wave on the evaporation/combustion of suspended droplet
Journal of the Korean Society of Propulsion Engineers, volume 6, issue 3, 2002, Pages 53~60
This paper presents the results of the experimental investigation on the effect of acoustic wave on the combustion of suspended A-1 jet fuel droplets in atmospheric pressure. Experimental results indicate that A-1 jet fuel droplet burning rate constants
were independent of initial droplet size and the relative evaporation/burning-rate constant
(ratio of the acoustically disturbed evaporation/burning-rate constant to the undisturbed evaporation/burning-rate constant) increased remarkably 1.2~1.51times, 1.04~1.42times, for frequency below 100Hz, and sound pressure level above 80dB.