The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算学方法求解二维线化欧拉方程对阵风与叶栅的干涉噪
进行了数值模拟。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算学方法求解二维线化欧拉方程对阵风与叶栅的干涉噪
进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅的非定常分 离、粘性效应跨音激波对失速颤振的影响
为当前
弹性力学的 主要难点。
明:以上例句、词性分类均由互联网资源自
,部分未经过人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算气动声学方法求解二维线化欧拉方程与叶栅的干涉噪声进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅的非定常分 离、粘性效应跨音激波
失速颤振的影响成为当前气动弹性力学的 主要难点。
声明:句、词性分类均由互联网资源自动生成,部分未经过人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算气动声学方法求解二维线化欧拉方程对阵风与叶涉噪声进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶非定常分 离、粘性效应
跨音激波对失速颤振
影响成为当前气动弹性力学
主
。
声明:以上例句、词性分类均由互联网资源自动生成,部分未经过人工审核,其表达内容亦不代表本软件观
;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算声学方法求解二维线化欧拉方程对阵风与叶栅的干涉噪声进行
模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅的非定常分 离、粘性效应跨音激波对失速颤振的影响成为当前
性力学的 主要难点。
声明:以上例句、词性分类均由互联网资源自生成,部分未经过人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
计算气动声学方法求解二维线化欧拉方程对阵风与叶栅的干涉噪声进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅的非定常分 离、粘性效应跨音激波对失速颤振的影响成为当前气动弹性力学的 主要难点。
声明:以上例句、词性分类均由互联网资源自动生成,部分人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算气动声学方法求解二维线欧
方程对阵风与叶栅的干涉噪声进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅的非定常 离、粘
效应
跨音激波对失速颤振的影响成为当前气动弹
力学的 主要难点。
声明:以上例句、词均由互联网资源自动生成,部
未经过人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算气动声学方法求解二维线化欧拉方程对阵风与叶栅的干涉噪声进行了数值模。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
叶栅的非定常分 离、粘性效应
跨音激波对失速颤
的影响
前气动弹性力学的 主要难点。
声明:以上例句、词性分类均由互联网资源自动生,部分未经过人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算气动方法求解二维线化欧拉方程对阵风与叶栅
干
进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅非定常分 离、粘性效应
跨音激波对失速颤振
影响成为当前气动弹性力
要难点。
明:以上例句、词性分类均由互联网资源自动生成,部分未经过人工审核,其表达内容亦不代表本软件
观点;若发现问题,欢迎向我们指正。
The gust-cascade interaction noise was numerically simulated using computational aeroacoustics by solving the two-dimensional linearized Euler equations.
采用计算气动声学方法求解二维线化欧拉方程阵风与叶栅的干涉噪声进行了数值模拟。
The main difficulty on the study of aeroelasticity lies in the effects of unsteady separation, shock and viscosity to the stall flutter.
振荡叶栅的非定
、粘性效应
跨音激波
颤振的影响成为当前气动弹性力学的 主要难点。
声明:以上例句、词性类均由互联网资源自动生成,部
未经过人工审核,其表达内容亦不代表本软件的观点;若发现问题,欢迎向我们指正。