• Journal of the Society of Naval Architects of Korea
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• v.36 no.3
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• pp.29-40
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• 1999

A numerical method in frequency domain for the analysis of the acoustic wave equation governing the sound field generated by a non-cavitating propeller under a steady of unsteady loading condition is developed. Theory shows that only multiples of the blade passage frequency exist and that the wave number consists of the frequency component due to the nonuniformity of the wake and the Doppler effect originated from the rotation of the blades. Correlation with experiments for a two bladed propeller, designed to be load-free at a particular advance speed, indicate that the thickness effect can be significant in steady case, but can be negligible compared to the unsteady loading effect.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.469-478
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• 2019

Multirotor configurations such as VTOL and urban air mobility have been focused on today due to the high maneuverability. Aerodynamic and aeroacoustic characteristics of multirotor have much difference to those of a single rotor. In this study, a numerical analysis based on the free wake vortex lattice method is used for identifying the wake interaction effect. In order to compare the various configurations and operating conditions, the effects of the spacing between the rotors in hovering flight and the effects of the advancing ratio and the formation in forward flight are discussed. In the hovering flight, the unsteady loading of multirotor changes periodically and loading fluctuation increases as decreasing the spacing. It causes the variation in unsteady loading noise and the noise directivity pattern. In the forward flight, the difference in loading fluctuation and noise characteristics are observed according to the diamond and square formation of rotors. By comparing with results of single rotor analysis, multirotor configurations have different directivity pattern and amplitude of loading noise according to the location of each rotor. As a result, wake interaction effect becomes a highly important factor for aerodynamic and aeroacoustic analysis according to multirotor configurations and operating conditions.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.2
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• pp.39-45
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• 2005

The aim of this research is to predict the thickness and loading noise of the round-tip shaped Hartzell propeller currently used in the general aviation aircraft. Before implementing the noise analysis, the pressure distribution on the propeller was obtained by using the free wake panel method and unsteady Bernoulli's equation. The noise signal at observer position can be obtained by using the FW-H equation. The noise prediction results for the propeller indicates that the thickness noise has s symmetric directivity pattern with respect to the tip path plane, while the noise due to loading shows higher noise directivity toward downstream than the upstream direction from the rotor plane. The loading noise is dominant rather than the thickness noise in normal operating condition.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.04a
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• pp.492-497
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• 2011

Helicopter uses a rotor system to generate lift, thrust and forces, and its aerodynamic environment is generally complex. Unsteady aerodynamic environment arises such as blade vortex interaction. This unsteady aerodynamic environment induces vibratory aerodynamic loads and high aeroacoustic noise. Those are at N times the rotor blade revolutions (N/rev). But conventional rotor control system composed of pitch links and swash plate is not capable of adjusting such vibratory loads because its control is restricted to 1/rev. Many active control methodologies have been examined to alleviate the problem. The blade using active control device manipulates the blade pitch angle at arbitrary frequencies. In this paper, Active Trailing-edge Flap blade, which is one of the active control methods, is designed to modify the unsteady aerodynamic loads. Active Trailing-edge Flap blade uses a trailing edge flap manipulated by an actuator to change camber of the airfoil. Piezoelectric actuators are installed inside the blade to manipulate the trailing edge flap.

• Proceedings of the Acoustical Society of Korea Conference
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• 1998.06c
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• pp.461-464
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• 1998

수중 프로펠러의 비공동 소음을 수치적으로 해석하였다. Ffowcs Williams-Hawkings 형태의 음향상사 방정식을 시간영역에서 해석하였으며 임의의 형상과 하중조건을 가지는 프로펠러의 소음 예측이 가능하도록 하였다. 또한 좌표계 변환을 통해 관찰자에 대해 상대적 운동이 있는 경우에도 소음 예측이 가능하도록 하였다. 균일/비균일 유입류 조건을 갖는 수중 프로펠러에 대해 소음 해석을 수행하였고 각각의 조건에 대해 음원별 소음 강도와 방향성을 예측하였다. 수치 해석결과 프로펠러 표면상의 압력 변화에 따른 비정상 하중에 의한 이중극 소음이 지배적인 것으로 나타났다. 이러한 음원별 접근법은 수중 프로펠러의 운용시 지배적인 소음원을 구별하고 그 특성을 파악하여 적절한 소음 제어책을 마련하는 기반이 될 것이다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2008.04a
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• pp.140-143
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• 2008

Experiments are performed to consider the ground effects on unsteady loading and acoustic generation. Partially inclined plate is used to maximize the unsteadiness of the rotor. Indirect method to recognize the unsteady effect is used by measuring the noise in the normal direction from the rotor plane. The experiment is conducted with a square plate of about $9m^2$ and one half of the plate is placed parallel with the rotor plane and the other half is inclined. The height of the plate and the angle of the inclined plate can be changed. Helicopter noise is also measured at the 4 different positions to study the directivity of the rotor noise. The distance between microphone and rotor hub is 1.3m. Tonal noise and broad band noise are measured and analyzed. Thickness noise, steady loading noise and unsteady loading noise are investigated from the rotor noise measurement.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.868-874
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• 2007

Noises from the helicopter rotor model are calculated numerically at various pitch angles. The aerodynamic data are calculated by using prescribed wake model and unsteady panel method. The distribution of aerodynamic loads on the blade surface are obtained from $0^{\circ}$ to $9^{\circ}$ pitch angles with equiangular increments of $1.5^{\circ}$. Although thickness noise is not related to the change of pitch angles, loading noise level increases about 3~4dBA every $1.5^{\circ}$ increment of pitch angle. The additive noise level shows sufficient value to perceive the loudness. From the result of directivity pattern the sound level at the lower region of the blade disc plane is higher than that of the upper region.

• Proceedings of the KSME Conference
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• 2002.08a
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• pp.763-766
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• 2002

A BEM is highly efficient method in the sense of economic computation. However, boundary integration is not easy for the complex and moving surface e.g. in a rotating blade. Thus, Kirchhoff surface is designed in an effort to overcome the difficulty resulting from complex boundary conditions. A Kirchhoff surface is a fictitious surface which envelopes acoustic sources of main concern. Acoustic sources may be distributed on each Kirchhoff surface element depending on its acoustic characteristics. In this study, an axial fan is assumed to have loading noise as a dominant source. Dipole sources can be computed based on the FW-H equation. Acoustic field is then computed by changing Kirchhoff surface on which near-field is implemented, to analyze the effect of Kirchhoff surface on it.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1995.10a
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• pp.104-110
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• 1995

지반과 구조물의 동적 상호작용은 건설분야에서의 중요한 현상으로, 특히 지반을 통해 인근구조물로 전달되는 진동은 구조물 자체의 구조적인 문제 뿐 아니라 그 속에 거주하는 사람이나 설비에 대한 안전성 또는 사용성에 나쁜 영향을 야기할 수 있다. 본 논문에서는 이러한 진동을 저감시키기 위해, 지반내에 정상적인 진동전파를 방해하는 구조물을 시공하여 진동 저감효과를 만들어 내는 방법을 연구하였다. 이러한 연구의 발상은 다음과 같다. 충진지반에서의 지반진동의 진폭을 해석하면서 진동의 크기가 기저암의 위치에 따라 큰 영향을 받는 것을 알았고 이로부터 지반내에 인위적인 층을 만들수 있다면 지반진동의 크기를 변화시킬 수 있지 않을까라는 생각에서 본 연구를 시작하였다. 또한 지반 내에서의 정상적인 진동의 전파를 방해하기 위한 차진 구조물을 만드는 방법은 연약지반의 강도중대 또는 차수의 목적으로 주로 사용하고 있는 그라우팅공법의 사용이 가능할 것이므로, 기존의 그라우팅현장에서 만들어진 지반의 물성치들을 사용하여 경계요소법에 의한 수치해석적 방법을 택하였다. 본 연구에서는 그라우팅공법의 시공성에 관한 것은 포함되지 않는다. 본 논문에서는 지반의 구조를 경사구조와 수평지반구조라는 두가지 특징적인 경우에 대해 검토하였다. 이중 경사진 기저암층을 가진 지반의 경우에는 기저암에서 진동의 비대칭적인 반사에 의해 수평기저암에서와는 달리 기저암의 한쪽에서 다른쪽에 비해 큰 진동이 발생한다. 그라우팅층의 효과를 검토하기 위한 연구의 순서는 일정주파수의 조화진동에 대해 먼저 여러 가지 크기의 그라우팅층과 함께 블록으로 볼 수 있는 크기의 그라우팅층에 대해 진동저감효과를 해석하였고, 이를 통해 보강층의 소요크기 및 최적위치를 구하였다. 사용된 물성치는 실제 지하철 건설현장에서 나타난 지반물성치 및 그라우팅후의 지반강도 및 전단파전파속도를 이용하였다. 또한 마지막에서 검토된 기차하중에 대한 효과를 알아보기 위해 사용된 기차운행에 의한 지반가속도도 역시 측정된 값을 사용하였다. 그러나 당시의 기차운행속도가 낮아 정상적인 운행에서는 더 큰 값이 나올 것으로 판단되었으나 측정된 값을 그대로 사용하였다.