• Transactions of the Korean Society of Mechanical Engineers B
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• v.25 no.4
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• pp.507-513
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• 2001

Time averaged pressure distributions in a high-speed centrifugal compressor channel diffuser at design and off-design flow rates are investigated. Pressure distributions from the impeller exit to the channel diffuser exit are measured for various flow rates from choke to near surge condition, and the effects of operating condition are discussed. The strong non-uniformity in the pressure distribution is obtained over the vaneless space and semi-vaneless space caused by the impeller-diffuser interaction. As the flow rate increases, flow separation near the throat, due to large incidence angle at the vane leading edge, increases aerodynamic blockage and reduces the aerodynamic flow area downstream. Thus the minimum pressure location occurs downstream of the geometric throat, and it is named as the aerodynamic throat. And at choke condition, normal shock occurs downstream of this aerodynamic throat. The variation in the location of the aerodynamic throat is discussed.

• Proceedings of the KSME Conference
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• 2000.04b
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• pp.548-554
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• 2000

The aim of this paper is to understand the time averaged pressure distributions in a high-speed centrifugal compressor channel diffuser at design and off-design flow rates. Pressure distributions from the impeller exit to the channel diffuser exit are measured and discussed far various flow rates from choke to near surge condition, and the effect of operating condition is discussed. The strong non-uniformity in the pressure distribution is obtained over the vaneless space and semi-vaneless space caused by the impeller-diffuser interaction. As the flow rate increases, flow separation near the throat, due to large incidence angle at the vane leading edge, increases aerodynamic blockage and reduces the aerodynamic flow area downstream. Thus the minimum pressure location occurs downstream of the geometric throat, and it is named as the aerodynamic throat. And at choke condition, normal shock occurs downstream of this aerodynamic throat. The variation in the location of the aerodynamic throat is discussed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.6
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• pp.496-502
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• 2018

In this study, experimental and analytical studies were carried out to observe the phenomenon of aerodynamic throat formed according to the primary flow and secondary flow momentum of the ejector. The equilibrium interval of the aerodynamic throat, which is the main variable of the ejector performance, was observed through the experiment using the cold flow experiment and the analysis using FLUENT. Performance characteristics were investigated by the change of the primary flow rate and the throat diameter of the ejector cylinder. As a result, the performance of the standard ejector was confirmed to be within the range of 0.33~1.167(off-design/design) and cylinder throat diameter range of 1~1.17(off-design/design area ratio).

• Journal of the Korean Society of Laryngology, Phoniatrics and Logopedics
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• v.11 no.2
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• pp.146-160
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• 2000

The current study aimed to establish rationales for using three different voice therapies (resonant voice, accent method, and tongue-tip trills) by comparing the aerodynamic, and vocal fold closure characteristics under three therapies. A total of 8 male under/graduate students(tenors) participated as subjects. In order to compare aerodynamic characteristics, air flow rates and subglottal pressures were measured using Phonatory function analyzer under three therapy conditions. The characteristics of vocal fold closure patterns also were examined by comparing closed quotients(CQ) measured by Electroglottograph(EGG) under three therapy conditions. However, maximum phonation time (MPT) was measured under only resonant voice and tongue-tip trills using Aerophone II. The results are summarized as follows : 1) CQ, subglottal pressure and MPT decreased significantly under resonant voice as compared with throat voice, but the air flow rate increased significantly under resonant voice. 2) CQ decreased significantly under accent method as compared with throat voice, but both air flow rate and subglottal pressure increased significantly under accent method. 3) Both CQ and MPT decreased significantly under tongue tip trills as compared with throat voice, but air flow rate and subglottal pressure increased significantly under tongue-tip trills. Clinical implications of results were discussed in light of differential effects of three voice therapies.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.275-278
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• 2010

By changing the nozzle throat area during the operation, thrust of a pintle thruster can be adjusted easily such as a liquid propulsion. In this paper, numerical analysis was carried out for SNECMA's pintle thruster with different pintle shapes. Flow field and aerodynamic load changed drastically with pintle shapes. Bore in the pintle decreased aerodynamic load significantly.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.189-192
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• 2011

In solid rockets, a pintle thruster is a modulatable thrust device which controlls nozzle throat area. In this study, effect of bore on aerodynamic loads in a SNECMA modulatable thruster was carried out. Existence of bore resulted in reduced aerodynamic load.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.29 no.12 s.243
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• pp.1285-1290
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• 2005

A theoretical analysis of an annular injection supersonic ejector equipped with a second-throat was developed under the assumption that the secondary flow is choked aerodynamically by interaction with primary flow in the mixing chamber. The predicted secondary flow pressure agrees reasonably well with the measurements. Using the analysis, the compression ratio, the secondary flow Mach number, and the location of the choking point were presented in terms of entrainment ratio.

• Journal of the Korean Society of Laryngology, Phoniatrics and Logopedics
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• v.26 no.2
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• pp.112-116
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• 2015

Background and Objectives : Aerodynamic analysis is an examination which provides information regarding various vocalization measures indicating laryngeal efficiency. Voice evaluation using such examination must be capable of distinguishing between normal to abnormal voice. It also observes variables on aerodynamic characteristics by gender in regards to patients of vocal disorders, especially of vocal cord paralysis and vocal polyp, and compares the conditions before and after surgery. This paper therefore, seeks to build a framework for establishing standard levels of aerodynamical characteristic on vocal disorders. Subjects and Methods : The study was intended for a total number of 20 patients with vocal polyp or unilateral vocal cord paralysis. Those with the vocal polyp underwent laryngomycroscopy surgery and the vocal cord paralysis, vocal fold injection using Restylane. Aerodynamic analysis fulfilled the Maximum sustained Phonation (MXPH) and Voicing Efficiency (VOEF) by using PAS Model 6600 (KayPENTAX, USA). Results : In MXPH, increase in PHOT were evident with vocal polyp after surgery. As for patients with vocal cord paralysis, MAXDB, MEADB, DHODB, PHOT all have increased and MEAP, PEF, MEAF decreased after surgery. In VOEF, patients with vocal cord paralysis who underwent surgery showed increase in MAXDB, MEADB, DHODB, FET100, ARES, but decreases in PEF, TARF. Conclusion : Overall, it can be concluded that patients with the vocal polyp and vocal cord paralysis seemed to get closer to the normal values after than before surgery in majority of measures. This confirms that the function of their vocal cord has improved nearly to normality through operations.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.3
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• pp.1-9
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• 2017

Numerical computations are performed to investigate the effect of pintle stroke on the performance of an internal pintle thruster. Results show that the thrust control ratio was less than 2% and the aerodynamic load ratio was 22% as the pintle stroke increased. The flow past the nozzle throat rapidly expanding because of the shape of the pintle, and a shock wave was generated. Particularly, at the pintle stroke distance of 4 and 5 mm, the shock wave hit the wall of the nozzle, results in peeling bubbles. Depending on the altitude, the thrust increased and the aerodynamic load decreased, but the difference was as small as 1.5%. In the presence of the bore, the reduction of the pintle tip area resulted in a decrease in aerodynamic load.

• Advances in aircraft and spacecraft science
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• v.3 no.4
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• pp.367-378
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• 2016

Thrust Vectoring is a dynamic feature that offers many benefits in terms of maneuverability and control effectiveness. Thrust vectoring capabilities make the satisfaction of take-off and landing requirements easier. Moreover, it can be a valuable control effector at low dynamic pressures, where traditional aerodynamic controls are less effective. A numerical investigation of Fluidic Thrust Vectoring (FTV) is completed to evaluate the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. The methodology presented is general and can be used to study different techniques of fluidic thrust vectoring like shock-vector control, sonic-plane skewing and counterflow methods. For validation purposes the method will focus on the dual-throat nozzle concept. Internal nozzle performances and thrust vector angles were computed for several range of nozzle pressure ratios and fluidic injection flow rate. The numerical results obtained are compared with the analogues experimental data reported in the scientific literature. The model is integrated using a finite volume discretization of the compressible URANS equations coupled with a Spalart-Allmaras turbulence model. Second order accuracy in space and time is achieved using an ENO scheme.