定几何二元倒置“X”型混压式超声速进气道实验

Experiment on Fixed-Geometry Two-Dimensional Mixed-Compression Supersonic Inlet with Sweepforward High-Light and "X"-Type Missile Configuration

针对一种定几何二元倒置“X”型布局的混压式进气道进行了风洞吹风实验，得到了进气道的性能并进行了分析。结果表明，随着来流马赫数的增加，进气道总压恢复系数不断减小，流量系数却先增加，在设计点达到最大值后减小。当迎角变化时，迎背风侧进气道呈现不同的特性，在小迎角α〈6°状态下，背风侧进气道总压恢复系数先上升后下降，迎风侧进气道总压恢复系数却保持一直缓慢下降，在流量系数方面，背风侧进气道流量系数一直增加而迎风侧减小，但两侧总的流量变化不大；在大迎角（α=6-9°）状态下，背风侧进气道总压恢复系数和流量系数均下降剧烈，而迎风侧进气道总压恢复系数虽有下降但流量系数却有所上升。本文为倒置“X”型进气道的设计提供了实验依据。

A fixed-geometry two-dimensional mixed-compression supersonic inlet with sweepforward high-light is tested in a wind tunnel. The inlet is designed in an ＂X＂ type missile configuration . Results indicate that. （1） The total pressure recovery decreases with the increase of the free stream Mach number, while the mass flow ratio keeps increases firstly and then declines rapidly, the maximum value is obtained at the design point. （2） When the angle of attack is rised less than 6°, the total pressure recovery of the flow in the lee side inlet increases and then falls, while the windward side inlet retains decreasing; the mass flow ratio of lee side inlet keeps ascent and the windward side inlet goes down so that the summation of both sides is almost constant. （3）When the angle of attack is rised from 6° and 9°, both the total pressure recovery and the mass flow ratio of the lee side inlet fall quickly, and the total pressure recovery of the windward side inlet also decreases, but its mass flow ratio increases. An example is provided for the design of the type inlet.