研究了局域能量脉冲注入条件下高超声速进气道流场的扰动情况。数值模拟采用三维雷诺平均N-S方程，分别利用ROE格式和二阶中心格式对对流通量和粘性通量进行离散处理；用高斯-赛德尔隐式格式对方程进行时间推进求解，采用k-ε两方程模型用于湍流的数值模拟。开展了高超风洞平板流场能量注入实验，获取了高速纹影图像，并对实验结果与计算结果进行比较。研究表明，能量注入产生的冲击波能与高超流动产生的斜激波发生强烈干扰，脉冲能量的引入可能引起高超声速进气道流量俘获率产生剧烈震荡，从而导致进气道流场的性能急剧下降。

Scramjet inlet flow disturbance was studied for the case when energy impulse was added on the wall of scramjet inlet. The flow is governed by the the 3-D Reynolds averaged Navier-Stokes equations. To split the viscosity flux and the convective flux of the N-S equations, the second order central scheme and the ROE scheme were adopted respectively. With the implicit Gauss-Seidel scheme, the code was advanced in time. The k-ε turbulence model was used for turbulence simulations. The characteristics of hypersonic flat with energy addition were tested in a hypersonic tunnel by applying a high speed schlieren system. The results show that the numerical pressure contour agrees well with the experimental schlieren photograph. Energy addition could induce strong shock wave interaction which might change the mass flow rate of scramjet inlet sharply. In other words, energy addition can decrease the performance of scramjet inlet flow and inlet unstart might take place at this rate.