该方法适用于轴对称流场的瞬态测试，具有宽带和非接触的特点。
This measurement system, particularly suitable for instantaneous detection of axisymmetrical shock waves, is broadband as well as non-contact.
本文论述了入射激波与飞行器头部激波相交后的二维或轴对称干扰流场的计算方法。
This paper describes the numerical method determining two-dimensional and axisymmetric flow for head-on vehicle shock-planar incident shock interaction.
因此对它的求解，要较相应另攻角轴对称绕流的二点边值问题简便。
Therefore, the solutions can be obtained more easily than that of two point boundary value problems of axisymmetric flow case.
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