1. Finally the feasibility of spectral element methods for Computational Aeroacoustics is verified.
最终证明了谱元方法求解计算气动声学问题的可行性。
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2. Overlap grid is selected for helping calculate aeroacoustics following and apply symmetrical boundary condition.
为方便后面声场的计算和对称边界条件的实施，选用重叠网格。
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3. A computational aeroacoustics approach is applied to studying sound propagation in subsonic and supersonic nozzle.
采用计算气动声学方法研究了管道近音速区的声传播和声波与激波的相互作用问题。
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4. The research on the rotor blade-vortex interaction (BVI) noise is a very important aspect and a very challenging subject in the rotorcraft aeroacoustics field.
旋翼桨-涡干扰噪声问题是直升机气动声学领域的一个研究热点和难点。
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5. The paper presents a finite volume numerical method universally applicable for solving both linear and nonlinear aeroacoustics problems on arbitrary unstructured meshes.
介绍了有限体积数值方法，该方法适用于在任意非结构网格上求解线性和非线性的航空声学问题。
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6. In this article spurious waves introduced in the computation of aeroacoustics are analyzed theoretically and filters are proposed to attenuate these waves as soon as they are generated.
从理论上分析了数值伪波产生的原因，要消除数值伪波可用滤波方法。
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7. In this paper, the numerical methods, issues and development for aeroacoustics, were described, including finite difference scheme, boundary conditions and nonlinear acoustics and shocks.
本文介绍了气动声学数值计算的方法和有关的问题、边界条件的处理以及计算非线性声波的数值方法和进展。
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8. In this paper, the numerical methods, issues and development for aeroacoustics, were described, including finite difference scheme, boundary conditions and nonlinear acoustics and shocks.
