来流速度的英文

• inflow velocity

• "来"英文翻译    come; arrive
• "流速"英文翻译    velocity of flow; strength; ...
• "度"英文翻译    surmise; estimate
• "流速，速度" 英文翻译 :    velocity
• "流速度" 英文翻译 :    seepage velocity
• "来流" 英文翻译 :    incident flow; incoming flow; inflow
• "伴流速度" 英文翻译 :    wake speed; wake velocity
• "层流速度" 英文翻译 :    laminar velocity
• "潮流速度" 英文翻译 :    strength of current; tidal velocity
• "潮流速度差" 英文翻译 :    tidal current difference
• "出流速度" 英文翻译 :    discharge velocity
• "供流速度" 英文翻译 :    supply velocity
• "横流速度" 英文翻译 :    crossflow velocity
• "洪流速度" 英文翻译 :    flood velocity
• "环流速度" 英文翻译 :    circular velocity; speed of circulation
• "回流速度" 英文翻译 :    back flow velocity; back-flow velocity
• "挤流速度" 英文翻译 :    squish velocity
• "流速计，速度计" 英文翻译 :    velocimeter
• "漫流速度" 英文翻译 :    crossflow velocity
• "能流速度" 英文翻译 :    rate of energy flow
• "排出流速度" 英文翻译 :    outflow velocity
• "排流速度" 英文翻译 :    outflow velocity; velocity of retreat
• "喷流速度" 英文翻译 :    jet speed
• "偏流速度" 英文翻译 :    drift velocity
• "漂流速度" 英文翻译 :    drift velocity

• The vortex - vibration was measured when the towed velocity , dip angle between the circular cylider and flow velocity , and diameter were varied
  对不同拖曳速度、拖缆倾角，即拖缆与来流速度之间的夹角和不同直径的拖缆涡激振动进行了测量分析。
• A cascaded architecture is adopted , where desired propeller rate of revolution is generated by solving a static 2nd order equation with a parameter of desired thrust force , which is the input of the speed / position tracking control
  在推进器动态模型的基础上，采用滑模控制的方法，由速度位置误差获得期望推力，再通过求解包括来流速度的二次方程得到期望螺旋桨转速。
• At large attack angle the frequency of the vortex has n ' t a apparent zone of " lock - in " . the fluid - induced vibration at large attack angle belongs to the stable dynamic response problems . but a sudden skip of amplitude will occur at large inlet velocity
  在大攻角下分离涡脱落的频率没有一个明显的频率锁定区域，流体振动属于稳定的动力响应问题，但在大来流速度下会出现振幅突跳的现象。
• The influence of inflow velocity , the baffle body height and the clapboard position on the flow velocity , flow equilibrium between the two sides of the clapboard , particle distribution , rich / lean concentration ratio and flow resistance characteristic are studied numerically
  文章研究了来流速度，撞击块高度、隔板位置等因素对气相速度场、隔板两侧配风均匀性、颗粒浓度、浓淡分离比和燃烧器内阻力特性的影响。
• Results show that the influence of mainstream reynolds numbers on heat transfer coefficience is little and the heat transfer coefficience raise with the increase of reynolds numbers . the influence of the position of holes on heat transfer coefficience is complex and correlate with the mainstream speed and the balde surface curvature . and the influence of blowing ratio on heat transfer coefficience is more great ( especially to stator ) , and show a complex relation to mainstream reynolds number and the position of holes
  实验结果表明，不同孔位出流的换热由于孔排下游表面来流速度及叶片表面曲率的不同而有不同的规律，而主流雷诺数对叶片表面特别是压力面和前缘区域的换热系数比的影响较小，吹风比对换热系数影响较大(特别是导叶) ，并且随气膜孔位置和来流雷诺数的变化而情况复杂。
• The effects of such elements as primary flow total pressure , flow rate , degree of fuel rich , nozzle structure , flying speed and secondary combustion on ejecting mode performance were researched . it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0 . 7 . to deeply analyze thrust augmentation mechanism in low speed range , the research was further continued by changing secondary combustion organization and aft - body configuration
  研究了一次流总压、流量、富燃程度、喷管结构、二次流来流速度、二次燃烧组织对引射模态性能的影响，发现实验样机构型在0 . 7ma以上的飞行条件下可以获得推力增强，而在0 . 7ma以下无推力增强。
• In this dissertation , through computer simulation , the problems of modeling , control and guidance of auvs are presented . the first part of this dissertation addresses the problem of dynamically modeling of auvs , and derives thrusters " two - dimension nonlinear dynamic model , which has axial flow speed and propeller rotational velocity as two state variables , voltage or current of motor as inputs , and thruster force and torque as output . the second part focuses on the nonlinear adaptive sliding mode control of auvs in diving plane and steering plane
  本论文系统研究了自主式水下航行器的建模、非线性自适应滑模控制、以及深度调整和水平面导引方法等问题，具体成果和创新点如下1 、根据流体力学理论，建立了螺旋桨推进器的动态模型，它以螺旋桨来流速度v _ p和螺旋桨转速n为状态变量，以电机施加转矩为输入，螺旋桨推力t和转矩q为输出。
• Result of numerical simulation shows that the grads of continuous phase " s velocities decreases with the presence of microbubble of which the diameter is 100 / / w , the profiles of air volume fraction in the boundary layers is similar to triangle or echelon , affected by interaction among the particle , there is a saturated air fraction , within the scope of saturated air fraction , increasing the air injection ratio can accrete the friction reduction ratio , under the condition of same air injection ratio , the free - steam velocity is larger , the effect of friction reduction is worse
  计算结果表明，直径为100 m的微气泡能减小近壁面连续相的速度梯度；微气泡在边界层中的浓度分布近似为三角形或梯形分布；受粒子间相互作用的影响，存在一饱和浓度；减阻率随喷气量的增大而增大，直至饱和喷气量，此后，增大喷气量，壁面摩擦阻力变化不大；相同喷气量下，来流速度越大，减阻率越低。
• At first , the finite element formulation is presented to determine the flutter characteristics of laminated panels at elevated temperature . then both the linear and nonlinear panel flutter characteristics are analyzed . the panel flutter boundaries are finally determined and the effect of temperature , airflow speed , etc , on the panel flutter characteristics is analyzed
  为此，本文首先建立了复合材料壁板热颤振的有限元模型并对受热壁板的线性和非线性颤振特性进行了研究；最后确定了壁板的颤振边界，分析了温度、来流速度等因素对壁板颤振特性的影响规律。
• Firstly , the airfoil ' s classic flutter ( at small attack angle ) , stall flutter ( near the static stall angle ) and response ( at large attack angle ) are analyzed . it is found from the numerical results that " lock - in " will occur at certain freestream velocity range near the static stall angle , where the frequency of the vortex will be equal to the natural frequency and the flutter has the characteristic of self - induced oscillation . when the attack angle is far from the static stall angle , the vortex will have its own frequency , which differs from the natural frequency , and the flutter has the characteristic of forced oscillation
  首先研究了二维翼型的古典颤振(小攻角) 、失速颤振(失速攻角)和动力响应问题(大攻角) ，得到以下结论：在静态失速攻角附近的一定来流速度范围内，分离涡会发生频率锁定现象，分离流的频率与固有频率趋于相同，这时的振动呈现自激振动的特点；远离失速攻角时分离流频率则摆脱固有频率的影响，此时的振动具有强迫振动的特点。