• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.3
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• pp.252-258
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• 2017

This paper describes on introduction of CASE 3 for EFD-CFD comparison workshop which is incharged of aerodynamic subcommittee of The Korean Societry or Aeronautical and Space Science. In addition, the results of candidate for CASE 3 were compared with experimental result and computational result. Currently, for this case 3, there are eight candidates from company, university and research institute. According to comparison of their results, they are in accordance with experimental data and computational data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.1
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• pp.41-52
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• 2021

During atmospheric ascent of a launch vehicle, airborne acoustic loads act on the vehicle and its effect becomes pronounced at transonic speed. In the present study, acoustic loads acting on a hammerhead launch vehicle at a transonic speed have been analyzed using ��-ω SST based IDDES and the results including mean Cp, Cprms, and PSD are compared to available wind-tunnel test data. Mesh dependency of IDDES results has been investigated and it has been concluded that with an appropriate turbulence scale-resolving computational mesh, the characteristic flow features around a transonic hammerhead launch vehicle such as separated shear flow at fairing shoulder and its reattachment on rear body as well as large pressure fluctuation in the region of separated flow behind the boat-tail can be predicted with reasonable accuracy for engineering purposes.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.8
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• pp.21-29
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• 2002

In the present study, a passive control method, using a porous wall and cavity system, is applied to the shock wave/boundary layer interactions in transonic moist air flow. The two-dimensional, unsteady, compressible, Navier-Stokes equations, which are fully coupled with a droplet growth equation, are solved by the third-order MUSCL type TVD finite difference scheme. Baldwin-Lomax model is employed to close the governing equations. In order to investigate the effectiveness of the present control method, the total pressure loss of the flow and the time-dependent behaviour of shock motions are analyzed in detail. The computed results show that the present passive control method considerably reduces the total pressure losses due to the shock wave/boundary layer interaction in transonic moist air flow and suppresses the unsteady shock wave motions over the airfoil as well. It is also found that the location of the porous ventilation significantly affects the control effectiveness.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.3
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• pp.259-267
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• 2017

Flow fields around a KARI-11-180 airfoil, SDM and transonic body are numerically simulated by using an unstructured meshes based compressible flow solver developed at KAIST. RANS equations are solved to analyse the flow fields and Roe's FDS method is adopted to evaluate convective fluxes. Turbulence effect of the flow fields is modeled by a SA model, SST model and ${\gamma}-{\widetilde{Re}}_{{\theta}t}$ model. It is found that smaller drag coefficients are predicted for the KARI-11-180 airfoil when a transition phenomenon is considered and small deviations exist between CFD and EFD results. For the SDM, flow separation is observed at a leading edge and calculated aerodynamic properties show similar tendencies to experimental results. A shock wave on main wings of the transonic body is successfully captured by the present flow solver at a Mach number 0.9. Estimated pressure profiles by means of the present CFD method also agree well with those of wind tunnel results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.6
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• pp.457-464
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• 2021

To analyze the buffet phenomenon that causes serious vibration loads on a satellite launch vehicle, the pressure fluctuations on a hammerhead launch vehicle at transonic speeds are predicted by coupling CFD analysis and semi-empirical methods. From the RANS simulation, shock oscillation region, separation region, and separation reattachment region are identified, and the boundary layer thickness, the displacement thickness, and flow properties at boundary layer edge are calculated. The pressure fluctuations and power spectra on the hammerhead fairing are predicted by coupling RANS results and semi-empirical methods considering spatial distribution, and compared with the experimental data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.581-585
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• 2007

Sonic arc airfoil derived from the TSD theory is modified to new airfoil shape and its aerodynamic performance in transonic flow is investigated. The numerical simulation using Euler equations for the modified sonic arc airfoil is performed. The numerical results are compared with the aerodynamic performance of NACA0012 airfoil, of supercritical airfoil, and of NACA64A210 airfoil. In the same free stream Mach number of transonic flow, the pressure drag of the modified sonic arc airfoil is smaller than that of NACA0012 airfoil and the lift-drag ratio of the modified sonic arc airfoil is much larger than that of NACA0012 airfoil. In the comparison of the drag-divergence Mach number of transonic flow, the drag-divergence Mach number of the modified sonic arc airfoil is larger than that of NACA64A210 airfoil but is smaller than that of supercritical airfoil.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.39 no.6
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• pp.477-483
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• 2015

Investigations into cavity flows have been conducted for noise and vibration problems that arise in cavity systems. Cavity systems have been applied in engineering devices and have undergone rapid development in the aerospace industry. Meanwhile, to the author's best knowledge, the cavity on a curved wall has been seldom studied. The present work is conducted to study the flow physics of a cavity mounted on a curved wall. Numerical analysis is performed to investigate the cavity flow. Two variables of sub- and supersonic cavity flows were considered: the radius of curvature of the curved wall (L/R) and the inlet Mach number. The results show that the uniform vortex generated by the cavity flow on the curved wall stabilize the pressure fluctuation as time passes. As the inlet Mach number increases, the pressure fluctuation amplitude increases. The results obtained from the curved wall are compared with those from a straight wall using Rossiter's formula. The Strouhal number of the curved wall is lower than that of the straight wall. Lower Strouhal numbers have been obtained in the present computational fluid dynamics (CFD) results than in the theoretical results using Rossiter's formula.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.36-36
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• 2000

천음속 또는 초음속 유동이 유동장의 하류에서 부여되는 압력조건에 의하여 감속되는 경우나, 유동방향의 갑작스런 변화를 요구하는 물체 혹은 벽면이 존재하는 경우에 발생한 충격파는 벽면을 따라 발생하는 층류 혹은 난류 경계층과 복잡한 상호간섭 (interaction)을 일으켜 충격파에 의한 박리 발생, 충격파 하류에 새로운 충격파 발생, 충격파가 큰 진폭으로 진동하게 되는 현상 등을 발생시킨다. 이러한 간섭현상은 고속유동이 통과하는 유체요소나 유체기기의 성능을 좌우하는 매우 중요한 유동현상으로, 유체기계의 설계 시 사전에 고려되어야 할 중요한 공학적 문제이다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.57-60
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• 2006

The instability analysis of submerged gas flow into liquid is studied, which assumes gas and liquid as viscous and irrotational. At low mass flow rate of gas, injected gas plume is collection of bubbles, and increase of gas flow rate makes plume as a jet. It is well known that the transition from bubbling to jetting occurs in the transonic region. But previous works neglect viscous effect of gas flow into liquid. This paper concerns about an application of viscous potential flow theory in cylindrical gas flow into liquid. The growth rate versus wave number and mach number is compared with various condition including inviscid and viscous flow.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.10-10
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• 1998

천음속 익형에서 발생하는 응축충격파와 경계층의 간섭을 피동제어 하여 항력감소에 대한 연구를 2.5$\times$7$\textrm{cm}^2$ 천음속 풍동에서 수행하였다. 익형표면에 설치한 정압공으로 정압을, 익형후방에 설치한 8개의 Pitot probe로 전압을 동시에 측정하여 충격파를 통한 에너지의 손실과 항력의 변화를 계산하였고, 또한 유동장과 충격파의 형상을 가시화하기 위해 슈리렌 가시화 시스템을 사용하였다. 실험은 NACA 0012 익형에서 기공률 변화에 따른 피동제어의 항력감소 초과를 조사한 다음 NACA 64-018 익형에서는 기공률과 공동의 크기의 변화가 미치는 효과를 연구하였다. 피동제어의 개념은 충격파가 발생하는 하부벽을 다공벽으로 만들고 그 아래를 공동으로 만들면 충격파 후방의 상대적으로 높은 압력이 기류의 일부를 공동으로 자연스럽게 유입시키고 다시 공동에서 낮은 압력의 충격파 상류로 유출시키는 것이다.