弓形激波

地球弓形激波中的湍动加热

Turbulence heating in earth 's bow shock

通过干涉照片获得了流场中六个截面的密度分布曲线，同时从阴影照片上测量出弓形激波的归一化脱体距离为0.046。

The normalized separate distance ( 0.046 ) of a bow shock wave is measured from the shadow photo .

利用动量定理和激波理论分析方法，提出了喷流等效体的概念，推导了等效体弓形激波方程。

Based on momentum theory and shock wave gas dynamic theory , jet equivalent body idea and bow sharp wave mathematic formula is brought forward .

研究了气体二次喷射中喷射位置、喷射角度、喷射孔形状、喷射马赫数、喷射流量等诸多参数对混合流场弓形激波的影响；

Effect on bow shock wave due to secondary gas injection was investigated with different Mach numbers , gas mass , jet nozzle shape , jet positions and angles .

欠膨胀超声速射流逆流的流场包含有多激波（如弓形激波和马赫盘）、接触间断和剪切层，其结构非常复杂。

The flowfields of an underexpanded jet counter to a supersonic stream containing multi shock ( e.g. bow shock and Mach disk ), contact discontinuities and shear layers are very complicated .

分析弓形激波后超音速喷流的流动结构及其非定常效应的形成机制，提出一种新的激波碰撞干扰流动的非定常形成机理。

The complicated flow structures of an unsteady supersonic jet behind the bow shock are analyzed and a new formation mechanism of the unsteady effect of the shock shock interference flow is proposed .

超音速导弹弹头发汗冷却数值模拟研究中，通过网格动态自适应方法以高分辨率精确捕捉到了弹头前弓形激波，研究了超音速气动加热下发汗冷却二次流、激波及边界层之间的相互作用。

Then the model was used to analyze transpiration cooling of a supersonic missile nosecone . The high resolution bow shock before the nosecone was snapped accurately by dynamic grid adaption . The interactions between the transpiration flow , the boundary layer and the bow shock were studied .

“朱诺号”携带的其中一台仪器，是用来测量带电粒子的无线电发射的。那些无线电波容易被转化成声波。探测器穿过“弓形激波”，即木星的磁场费力地穿过太阳风时形成的激波时，声波的音调发生巨变。

One of Juno 's instruments measures radio emissions from the charged particles , and those radio waves are easily converted into sound waves , which sharply changed in tone as the spacecraft crossed the " bow shock , " where Jupiter 's magnetic field plows through the solar wind .