The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验电弧加热式发动轴对称亚跨超音速流动进行
数值模拟,所采用的方法是矢
量分裂算法。
The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验电弧加热式发动轴对称亚跨超音速流动进行
数值模拟,所采用的方法是矢
量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加热发动基础上进行改进,设
盖发动
阳极的环形空腔,形成再生冷却
道。
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的观点;若发现问题,欢迎向我们指正。
The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验电弧加二维轴对称亚跨超音速流
进行了数值模拟,所采用的方法是矢
量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加基础上进行改进,设计了覆盖
阳极的环形空腔,形成再生冷却
道。
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
现问题,欢迎向我们指正。
The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要一实验电弧加热式发动机二维
亚跨超音速流动
行了数值模拟,所采用的方法是矢
量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加热发动机基础上行
,
计了覆盖发动机阳极的环形空腔,形成再生冷却
道。
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的观点;若发现问题,欢迎向我们指正。
The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验电弧加热式发动机对称亚跨超音速流动进行
数值模拟,所采用的方法是矢
量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加热发动机基础上进行改进,覆盖发动机阳极的环形空腔,形成再生冷却
道。
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的观点;若发现问题,欢迎向我们指正。
The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
一实验电弧加热式发动机二维轴
称亚跨超音速流动进行了数值模拟,所采用的方法是矢
量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加热发动机基础上进行改进,设计了覆盖发动机阳极的环空
,
再生冷却
道。
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 two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验加热式发动机二维轴对称亚跨超音速流动进行了数值模拟,所采用的方法是矢
量
裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有加热发动机基础上进行改进,设计了覆盖发动机阳极的环形空腔,形成再生冷却
道。
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 two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验热式发动机二维轴对称亚跨超音速流动进行了数值模拟,所采用的方法是矢
量
裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有热发动机基础上进行改进,设计了覆盖发动机阳极的环形空腔,形成再生冷却
道。
声明:以上例句、词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。
The two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验电弧加热式发动机二维轴对称亚跨超音速流动进行了数值模拟,所采用的方法是矢量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加热发动机基础上进行改进,设计了覆盖发动机阳极的环形空腔,形成再生冷却道。
声明:以上例句、词性分类均由互源自动生成,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 two-dimensional axisymmetric subsonic-transonic-supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method.
摘要对一实验电弧加热式发动机二维轴对称亚跨流动进行了数值模拟,所采用的方法是矢
量分裂算法。
An annular cavity placed around the anode of arcjet was designed to form a regenerative cooling channel on the base of an arc jet.
该文在原有电弧加热发动机进行改进,设计了覆盖发动机阳极的环形空腔,形成再生冷却
道。
声明:以例句、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的观点;若发现问题,欢迎向我们指正。