通过对ＥＦ２０００、Ｆ－１６Ｅ两个型号不同风格可调几何腹部进气道设计的分析，着重总结了Ｆ－１６多用途战斗机保形ⅢＢ进气道的成功设计经验，发现其调板过程中喉道位置的较大前移，加大了末激波的向前动程，是大马赫数下进气道工作不稳定性增大的主因。

Based on the investigation on the design of the variable geometry ventral inlets on the airplane EF2000 and F 16E,which are two different types of design,the successful and ripe design experiences of the proposed conformal Ⅲ B inlet configured on the F 16 multirole fighter are summarized and emphasised.It is found recently that with the forward movement of throat during the VGI diffuser ramp adjustment process,forward movement of the terminal shock is increased which is the main reason of the increasing instability of inlet operation at higher Mach number.It is desirable that the solving of instability problems in the similar variable ramp inlets may be benefit from the analysis.

V235.113