To study the flying principle of micro-air vehicle (MAV), and to economize the test outlay of wind tunnel, the numerical simulation of MAV is introduced in this paper.
为了研究微型飞行器的飞行机理以及节约风洞实验资金，进行了微型飞行器的数值模拟方法研究。
Three main methods, site measurement, wind tunnel test and numerical simulation techniques are commonly used for the study of wind-induced interference effects on buildings.
目前研究建筑物风致干扰效应的主要方法有现场实测，风洞模型试验和数值模拟计算三种方法。
The foreign countries have utilized the methods of wind tunnel test and numerical flow simulation, and carried out the series research on this problem.
国外利用风洞模型试验和流场数值模拟计算的方法，对此问题进行了系列化的研究。
The exact simulation of atmospheric boundary layer is not only the precondition of the wind tunnel test of the large span roof structures, but also a difficulty of its.
大气边界层的正确模拟是用风洞试验测量大跨屋面风荷载的前提，也是风洞试验研究的难点。
Comparison of structural shape coefficient determined by numerical simulation and wind tunnel test wind speed, wind direction on the shape coefficient of the degree structure.
通过不同风速、风向角下结构体形系数对比确定数值模拟及风洞试验中风速、风向角对结构体形系数的影响程度。
Wind vibration analysis based on numerical simulation mentioned above checked by the results gained time-history analysis based on wind tunnel test data is applied in this paper.
以基于风洞试验风压数据的风振时程分析结果为参考，对基于数值模拟的风荷载时程进行校核并应用于该结构的风振时程分析。
Compared with the traditional wind tunnel test, the simulation of vehicle outflow fields has several advantages: reproductively, short period and low cost.
与传统的风洞实验相比，汽车外流场的计算机数值模拟具有可再现性、周期短以及低成本的优点。
The reason of the effect of local configuration on wind pressure distribution is analyzed and the results of wind tunnel test and numerical simulation are compared with each other.
分析了局部构造对屋盖表面风荷载产生影响的原因，还将数值模拟结果与风洞试验结果进行了比较；
It is concerned in wind tunnel test, analytical analysis and numerical simulation.
研究方法有风洞实验、理论分析和数值模拟。
A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and high enthalpy wind tunnel test.
对一种带前体的高超声速矩转圆形进气道开展了数值仿真及高焓脉冲风洞试验研究。
A study is carried out on a hypersonic inlet with rectangular-to-circular shape transition and forebody using numerical simulation and high enthalpy wind tunnel test.
对一种带前体的高超声速矩转圆形进气道开展了数值仿真及高焓脉冲风洞试验研究。
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