• 한국추진공학회지
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• 제1권2호
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• pp.41-47
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• 1997

본 연구에서는 이중 orifice를 지나는 압축성 유동을 해석하기 위하여 압축성 유체에 대한 이론계산을 수행하였다. 이중 orifice의 단면적비, orifice 상류의 마하수 및 orifice 사이의 전압손실을 변화시켜, orifice로 인하여 발생하는 축류부에서 유동이 초우크하게 되는 조건을 구하였다. 본 연구의 결과로부터 유동의 초우크 현상은 orifice 단면적비뿐만 아니라 전압손실에도 의존함을 알 수 있다.

• 천문학회지
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• 제49권4호
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• pp.145-155
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• 2016

The Sausage radio relic is the arc-like radio structure in the cluster CIZA J2242.8+5301, whose observed properties can be best understood by synchrotron emission from relativistic electrons accelerated at a merger-driven shock. However, there remain a few puzzles that cannot be explained by the shock acceleration model with only in-situ injection. In particular, the Mach number inferred from the observed radio spectral index, M_radio ≈ 4.6, while the Mach number estimated from X-ray observations, M_X−ray ≈ 2.7. In an attempt to resolve such a discrepancy, here we consider the re-acceleration model in which a shock of M_s ≈ 3 sweeps through the intracluster gas with a pre-existing population of relativistic electrons. We find that observed brightness profiles at multi frequencies provide strong constraints on the spectral shape of pre-existing electrons. The models with a power-law momentum spectrum with the slope, s ≈ 4.1, and the cutoff Lorentz factor, γ_e,c ≈ 3−5×10⁴, can reproduce reasonably well the observed spatial profiles of radio fluxes and integrated radio spectrum of the Sausage relic. The possible origins of such relativistic electrons in the intracluster medium remain to be investigated further.

• 한국전산유체공학회지
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• 제17권3호
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• pp.53-58
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• 2012

Steady flow simulations through a high pressure turbine guide vanes were carried out. The main objective of the present work is to study the performance of turbulence models on the steady flow prediction from aerodynamic and aerothermal points of view. Three turbulence models were compared, namely SST, k-${\omega}$ and ${\omega}$-Reynolds stress models. The laminar results were also compared. The comparison was done with emphasis on the isentropic Mach number and heat transfer coefficient along the blade, and total pressure loss in the wake region. The calculated isentropic Mach number showed reasonable agreement with experimental data along the blade surface for all three turbulent models. For the total pressure loss in the wake region, ${\omega}$-Reynolds stress model showed the best agreement with the experimental data. However, unless using an appropriate transition model, the heat transfer coefficients of all three turbulent models showed poor agreement with experimental data.

• 대한기계학회논문집B
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• 제20권2호
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• pp.697-709
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• 1996

Supersonic axisymmetric jets issuing from various kinds of nozzles with a throat diameter of a few millimeters were experimentally investigated. The exit Mach number and Reynolds number based on the throat diameter of nozzle were in the range of 1.0 ~ 5.9 and 8.4$\times$ $10^4$ ~ 2.9$\times$$10^6$, respectively. The nozzle pressure ratio was varied from 5 to 85. Present paper aims to offer fundamental information of the supersonic free-jets, with an emphasis to give data with which the shape of the free-jets can be depicted under a specified condition. Experimental data are summarized to enable an estimation of the shape of the supersonic free-jets. The result shows that the shape of free-jets is dependent on only the nozzle pressure ratio.

• 한국항공우주학회지
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• 제31권5호
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• pp.10-17
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• 2003

정적으로 불안정한 비행선의 안전성을 확보하기 위해서는 동적 안정성이 필수적으로 요구된다. 본 연구에서는 강제진동 풍동시험을 보완하고 검증하기 위한 수치해석이 수행되었다. 비행선의 저속 유동장 해석을 위해 저마하수 예조건화된 수치기법이 적용되었다. 동적 감쇠계수의 변화를 두 가지 계산방법을 적용해 살펴보았다. 계산결과, 비행선은 각 방향의 모멘트에 대해 동적으로 안정되고, 힘에 대해서는 불안정하게 나타났다. 또한, 감쇠계수는 받음각과 각속도의 크기에 대한 영향보다 회전방향에 대한 영향이 더 큼을 확인하였다.

• 한국항공우주학회지
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• 제33권8호
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• pp.8-17
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• 2005

저속 압축성 유동에서 사용하는 예조건화 기법은 수렴성 증진에 효과적이다. 본 연구에서는 일반적인 오일러 지배 방정식과 각각 다르게 무차원화한 세 가지 종류의 예조건화 기법을 3차 공간 정확도의 MUSCL, DADI, 다중 격자, 국소 시간 전진 기법을 이용하여 2차원 비점성 bump 유동에 적용하였다. 결과적으로 국소 예조건화 기법에 전역 예조건화 기법의 압력 항 무차원화 방법을 적용하면, 마하수에 무관한 수렴 특성을 얻을 수 있다. 또한, 점근해석을 이용하여 각 예조건화 기법의 특성에 대해 언급하였다.

• 한국군사과학기술학회지
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• 제19권5호
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• pp.638-644
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• 2016

In this research, theoretical study on empirical analysis method to estimate waterdrop's deformation by shock wave is presented. Flow field is calculated using theoretical and empirical relations. Waterdrop's deformation including movement, size, mass, and orientation is modeled using empirical relations derived from existing experimental data. Developed method is applied to specific flight examples with arbitrary flight speed and vehicle's configuration. The flight speed is assumed to Mach number of 2 and 4. The diameter of waterdrop is varied from 1 to 5 mm. Waterdrops along the stagnation line in front of hemispherical nose with the radius of 50 mm and around a cone-shaped side wall with the half angle of 20 degree are considered. It is found that the maximum diameter of the waterdrop is increased up to 2.77 times the initial diameter. The mass is conserved more than 66.7 %. In the case of a cone-shaped side wall, waterdrop's orientation angles defined from the flight direction when the Mach number is 2 and 4 are calculated as 33.0 and 25.6 degree, respectively.

• 대한기계학회논문집B
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• 제21권10호
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• pp.1273-1283
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• 1997

Experiments of shock wave/turbulent boundary layer interaction were conducted by using a supersonic wind tunnel. Nominal Mach number was varied in the range of 1.6 to 3.0 by means of different nozzles. The objective of the present study is to investigate the effects of boundary layer flow bleed on the interaction flow field in a straight tube. Two-dimensional slits were installed on the tube walls to bleed the turbulent boundary layer flows. The bleed flows were measured by an orifice. The ratio of the bleed mass flow to main mass flow was controlled within the range of 11 per cent. The wall pressures were measured by the flush mounted transducers and Schlieren optical observations were made for almost all of the experiments. The results show that the boundary layer flow bleed reduces the multiple shock waves to a strong normal shock wave. For the design Mach number of 1.6, it was found that the normal shock wave at the position of the silt was resulted from the main flow choking due to the suction of the boundary layer flow.

• 대한기계학회논문집B
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• 제22권9호
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• pp.1229-1237
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• 1998

Experiments of shock-wave/turbulent boundary layer interaction were conducted by using a supersonic wind tunnel. Nominal Mach number was varied in the range of 1.6 to 3.0 by means of different nozzles. The objective of the present study is to investigate the effects of boundary layer suction on normal shock-wave oscillations caused by shock wave/boundary layer interaction in a straight duct. Two-dimensional slits were installed on the top and bottom walls of the duct to bleed turbulent boundary layer flows. The bleed flows were measured by an orifice. The ratio of the bleed mass flow to main mass flow was controlled below the range of 11 per cent. Time-mean and fluctuating wall pressures were measured, and Schlieren optical observations were made to investigate time-mean flow field. Time variations in the shock wave displacement were obtained by a high-speed camera system. The results show that boundary layer suction by slits considerably reduce shock-wave oscillations. For the design Mach number of 2.3, the maximum amplitude of the oscillating shock-wave reduces by about 75% compared with the case of no slit for boundary layer suction.

• 한국추진공학회지
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• 제2권3호
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• pp.36-46
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• 1998

초음속 유동에서 발생하는 충격파는 일반적으로 충격파 상류와 하류의 압력비에 의해 일반적으로 결정된다. 본 연구에서는 충격파의 진동현상을 규명하기 위한 연구의 일환으로, 미소교란법(small perturbation method)을 이용하여 이론해석을 수행하였으며, 충격파 하류의 유동장에 에너지 손실을 적용하여 충격파의 안정성을 이론적으로 해석하였다. 이론해석에서는 충격파 상류에 경계층 유동에서 발생하는 난류변동이나 주류에서의 압력변동이 충격파의 진동과 관련된다고 생각하여, 충격파 상류의 유동에 미소압력변동을 적용하여 충격파의 진동특성을 해석하였다. 본 연구의 결과들을 타 연구의 결과와 비교하였으며, 열선풍속계(hot wire)를 이용한 실험적 연구결과와 비교하였다.