angle of shock

angle of shock的基本解释

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冲击角

与angle of shock相关的网络例句 [注：此内容来源于网络，仅供参考]

With the decrease of Mach number of inflow, the total pressure recovery and the shock angle increase; the number of reflection of shock wave in the duct also increases, but the strength of the shock wave decreases.

对某典型高超声速侧压式进气道三维流场进行了数值分析，就壁面压力分布、波系结构和近壁流谱图与实验结果进行了比较，计算反映了流动的基本特徵。

The static model of torsion joint is based on that of bending joint. The effects of structure parameters inside air pressure, initial angle, rube average radius, rube shell thickness on the turning angle are analyzed and the following conclusions are drawn: the relationship between the angle of torsion joint and the inside air pressure is basically linear, the angle of torsion joint increases with the initial angle and rube average radius, the angle of torsion joint decreases while the rube shell thickness increases. The kinetic equation is built for torsion joint. Simulating experiment implies that the time of inflating and deflating process is extremely shorter than that of kinetic process. So the pneumatic process can be ignored in actual system design and control. The factors that affect the dynamic features of torsion joint, such as shell thickness of rubber tube, average radius, initial angle, connector's outlet area, moment of inertia and viscous damping coefficient, are analyzed and the following conclusions are drawn: the change of rube shell thickness has no effects on the dynamic process of FPA inside air pressure while greatly affects the turning angle of torsion joint; when the rube shell thickness is small, the torsion joint has a bigger turning angle, no overshoot and long risetime, when the shell thickness is big, the turning angle of torsion joint is small, but has high response speed, overshoot and low shock; when the rube average radius increases, the turning angle of torsion joint increases and the overshoot increases too; when the initial angle of torsion joint is big, the turning joint is big, the overshoot is small and shock is low, but the risetime is big; the connector's outlet area affects the dynamic process of FPA inside air pressure greatly, but has no effects on the dynamic process of turning angle; moment of inertia and viscous damping coefficient have no effects on the dynamic process of FPA inside air pressure, but affect the dynamic process of turning angle greatly.

在弯曲关节模型推导的基础上，建立扭转关节的静态模型，并分析了扭转关节内腔压力，初始转角，橡胶管平均半径，橡胶管壁厚等参数对关节转角的影响，得出扭转关节的转动角度与充入FPA内腔的压缩气体压力之间基本呈线性关系，扭转关节的转角随初始角度和橡胶管平均半径的增大而增大，扭转关节的转角随橡胶管壁厚的增大而减小的结论；建立了扭转关节的动力学方程，仿真实验表明FPA的充放气过程与扭转关节的动力学过程相比时间极短，在实际系统设计和控制过程中可以忽略不计；分析讨论橡胶管壁厚，平均半径，初始角度，气体节流口面积，转动惯量，粘性阻尼系数等因素对扭转关节动态特性的影响，得出橡胶管初始壁厚的变化对扭转关节FPA内腔压力的动态响应几乎没有影响而对关节转角的响应曲线影响比较明显，壁厚较小时，关节可以得到较大的转角，并且转角的响应曲线没有超调，但上升时间长，壁厚较大时，关节转角变小，响应加快，但是有超调和轻微振荡现象，橡胶管平均半径越大，得到的关节转角越大，但是转角响应的超调量也随之增大，FPA的初始角度越大，关节的转角越大，并且超调量减小，振荡减弱，但是上升时间增大，管接头出口面积的大小对关节FPA内腔压力的建立过程影响较大，但对关节转角的动态响应几乎没有影响，转动惯量和粘性阻尼系数对FPA内腔压力的动态过程几乎没有影响而对扭转关节转角有较大影响等结论。

The type of shock reflection over 50o wedge model is of regular reflection. The angle between the incident and reflection shock is also being increased as the model surface roughness increased. The flow visualization results indicate that the speed of reflection shock becomes slower.

在50度的模型实验条件下则会产生正规反射，当增加表面粗糙度后会使得射震波与反射震波之夹角增大，由上述两者结果可以发现，其结果可归因於反射震波之移动速度减缓所致，因此增加表面粗糙度必然会使震波反射有减弱的情况发生。

与angle of shock相关的网络解释 [注：此内容来源于网络，仅供参考]

detached shock wave：失速 stall 脱体激波

迎角 angle of attack | 失速 stall 脱体激波 detached shock wave | 波阻 wave drag